diff --git a/libs/question-bank/content/src/questions/081/081.01.json b/libs/question-bank/content/src/questions/081/081.01.json index f6e98cf9b..4201ae650 100644 --- a/libs/question-bank/content/src/questions/081/081.01.json +++ b/libs/question-bank/content/src/questions/081/081.01.json @@ -1,12 +1,12 @@ [ { "id": "Q0097R69DT", - "explanation": "", "learningObjectives": ["081.01.03.02.01"], + "explanation": "", "variants": { "PoIlhXRi": { - "id": "PoIlhXRi", "type": "simple", + "id": "PoIlhXRi", "question": "The lift formula is:\n(note: RHO = density)", "options": [ { @@ -42,12 +42,12 @@ }, { "id": "Q00RE4F94L", - "explanation": "", "learningObjectives": ["081.01.01.01.09"], + "explanation": "", "variants": { "y4FZDW2H": { - "id": "y4FZDW2H", "type": "simple", + "id": "y4FZDW2H", "question": "The pascal is the SI derived unit of pressure\nIt is equivalent to", "options": [ { @@ -83,12 +83,12 @@ }, { "id": "Q00YQLC8JS", - "explanation": "", "learningObjectives": ["081.01.09.02.07"], + "explanation": "", "variants": { "Cy1C8vfr": { - "id": "Cy1C8vfr", "type": "simple", + "id": "Cy1C8vfr", "question": "A deployed slat will:", "options": [ { @@ -124,12 +124,12 @@ }, { "id": "Q041RGQQ7E", - "explanation": "", "learningObjectives": ["081.01.03.02.01"], + "explanation": "", "variants": { "PtTYZdCk": { - "id": "PtTYZdCk", "type": "simple", + "id": "PtTYZdCk", "question": "A prototype aircraft is producing a value of lift of 850 Newtons. An engineer increases the wing area by 10%\nWhat is the new value of lift?", "options": [ { @@ -165,12 +165,12 @@ }, { "id": "Q057I3BA84", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "FQ3jGVKP": { - "id": "FQ3jGVKP", "type": "simple", + "id": "FQ3jGVKP", "question": "Drag is in the direction of – and lift is perpendicular to the:", "options": [ { @@ -206,12 +206,12 @@ }, { "id": "Q3LC2B6G99", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "5qmLIGXs": { - "id": "5qmLIGXs", "type": "simple", + "id": "5qmLIGXs", "question": "A positively cambered aerofoil will generate:", "options": [ { @@ -254,12 +254,12 @@ }, { "id": "Q06NLW5G1K", - "explanation": "", "learningObjectives": ["081.01.09.01.09"], + "explanation": "", "variants": { "W5QCBC8X": { - "id": "W5QCBC8X", "type": "simple", + "id": "W5QCBC8X", "question": "A crew plan for a full flap landing (30⁰) but, due to distraction, fail to extend flaps from the approach to the landing setting until a few seconds before touchdown. Which of the following statements is correct assuming the correct glidepath was flown to touchdown?", "options": [ { @@ -295,12 +295,12 @@ }, { "id": "Q0828WR0RH", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "bMtQh3sp": { - "id": "bMtQh3sp", "type": "simple", + "id": "bMtQh3sp", "question": "An aircraft decelerates from 1.4 V~S~ to 1.05 V~S~. What is the percentage increase in the lift coefficient (expressed as a percentage of C~LMAX~)?", "options": [ { @@ -336,12 +336,12 @@ }, { "id": "Q09G5TQRPC", - "explanation": "", "learningObjectives": ["081.01.01.01.17"], + "explanation": "", "variants": { "rXZMz1s7": { - "id": "rXZMz1s7", "type": "simple", + "id": "rXZMz1s7", "question": "The difference between IAS and TAS will...", "options": [ { @@ -377,12 +377,12 @@ }, { "id": "Q09GC6I4JJ", - "explanation": "", "learningObjectives": ["081.01.04.03.06"], + "explanation": "", "variants": { "5fGR3uoY": { - "id": "5fGR3uoY", "type": "simple", + "id": "5fGR3uoY", "question": "Which of these statements about induced drag are correct or incorrect?\n\n1. An elliptical spanwise lift distribution generates more induced drag than a rectangular lift distribution.\n\n2. Induced drag decreases with decreasing aspect ratio.", "options": [ { @@ -426,8 +426,8 @@ "explanation": "" }, "42dy7JZK": { - "id": "42dy7JZK", "type": "simple", + "id": "42dy7JZK", "question": "Which of these statements about induced drag are correct or incorrect?\n\n1. An elliptical spanwise lift distribution generates more induced drag than a rectangular lift distribution.\n\n2. Induced drag increases with decreasing aspect ratio.", "options": [ { @@ -460,8 +460,8 @@ "explanation": "" }, "lPjuHTKi": { - "id": "lPjuHTKi", "type": "simple", + "id": "lPjuHTKi", "question": "Which of these statements about induced drag are correct or incorrect?\n\n1. An elliptical spanwise lift distribution generates less induced drag than a rectangular lift distribution.\n\n2. Induced drag increases with decreasing aspect ratio.", "options": [ { @@ -497,12 +497,12 @@ }, { "id": "QJWX5BY25Y", - "explanation": "", "learningObjectives": ["081.01.09.02.08"], + "explanation": "", "variants": { "N7clGKRn": { - "id": "N7clGKRn", "type": "simple", + "id": "N7clGKRn", "question": "The purpose of correctly setting the leading and trailing edge devices on the wing of an aeroplane during take-off, approach and landing is to:", "options": [ { @@ -540,8 +540,8 @@ "explanation": "" }, "FDNWzu61": { - "id": "FDNWzu61", "type": "simple", + "id": "FDNWzu61", "question": "The purpose of correctly setting the leading and trailing edge devices on the wing of an aeroplane during take-off, approach and landing is to:", "options": [ { @@ -577,12 +577,12 @@ }, { "id": "Q0F2B5WPKW", - "explanation": "", "learningObjectives": ["081.01.05.03.01"], + "explanation": "", "variants": { "e1nmvzS0": { - "id": "e1nmvzS0", "type": "simple", + "id": "e1nmvzS0", "question": "If the speed during a straight and level flight is increased by a factor of 2, how will the parasite drag change? By a factor of:", "options": [ { @@ -618,12 +618,12 @@ }, { "id": "Q0JPEUCX2X", - "explanation": "", "learningObjectives": ["081.01.03.03.02"], + "explanation": "", "variants": { "jQdJD9IR": { - "id": "jQdJD9IR", "type": "simple", + "id": "jQdJD9IR", "question": "Refer to figure 081-10.\nAssuming all bodies have the same cross-sectional area and are in motion, which body will have the highest pressure drag?", "options": [ { @@ -656,8 +656,8 @@ "explanation": "" }, "y42UMaKI": { - "id": "y42UMaKI", "type": "simple", + "id": "y42UMaKI", "question": "Refer to figure 081-10.\nAssuming all bodies have the same cross-sectional area and are in motion, which body will have the lowest pressure drag?", "options": [ { @@ -693,12 +693,12 @@ }, { "id": "Q0KAXVZ57J", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "zCRCqdBa": { - "id": "zCRCqdBa", "type": "simple", + "id": "zCRCqdBa", "question": "An aircraft with trailing edge flaps and leading-edge slats is flying at a speed close to the clean wing stall speed when the flaps are extended to the landing configuration. The slats on the left wing remain retracted. If the speed is decreased, what are the possible consequences?", "options": [ { @@ -734,12 +734,12 @@ }, { "id": "Q0KEEL8PHA", - "explanation": "", "learningObjectives": ["081.01.12.01.03"], + "explanation": "", "variants": { "Ry33up3d": { - "id": "Ry33up3d", "type": "simple", + "id": "Ry33up3d", "question": "If ice is present on the leading edge of the wings, it may increase the landing distance due to a higher V~AT~ by as much as:", "options": [ { @@ -775,12 +775,12 @@ }, { "id": "Q0PMLL0FOH", - "explanation": "", "learningObjectives": ["081.01.04.03.02"], + "explanation": "", "variants": { "E2j7FlFR": { - "id": "E2j7FlFR", "type": "simple", + "id": "E2j7FlFR", "question": "The induced drag coefficient, CDi is proportional to:", "options": [ { @@ -816,12 +816,12 @@ }, { "id": "Q0RG54SOEY", - "explanation": "", "learningObjectives": ["081.01.04.03.04"], + "explanation": "", "variants": { "NQOkmrMZ": { - "id": "NQOkmrMZ", "type": "simple", + "id": "NQOkmrMZ", "question": "Assuming ISA conditions and an aircraft which is travelling at the same IAS, the drag of the aircraft at 6 000 ft, compared to the drag at sea level, will...", "options": [ { @@ -862,12 +862,12 @@ }, { "id": "Q0RHHTN1L0", - "explanation": "", "learningObjectives": ["081.01.03.02.05"], + "explanation": "", "variants": { "O6Poy1VU": { - "id": "O6Poy1VU", "type": "simple", + "id": "O6Poy1VU", "question": "An aircraft is flying at 1.9 Vs. What is the value of CL, compared with CLmax?", "options": [ { @@ -903,12 +903,12 @@ }, { "id": "Q0SSBEGKIB", - "explanation": "", "learningObjectives": ["081.01.04.03.02"], + "explanation": "", "variants": { "tcMhEgim": { - "id": "tcMhEgim", "type": "simple", + "id": "tcMhEgim", "question": "Excluding constants, the coefficient of induced drag (C~Di~) is the ratio of:", "options": [ { @@ -949,12 +949,12 @@ }, { "id": "Q0TOTISRIR", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "rp661AcZ": { - "id": "rp661AcZ", "type": "simple", + "id": "rp661AcZ", "question": "Coefficient of lift is:", "options": [ { @@ -990,12 +990,12 @@ }, { "id": "QB3TH86TDF", - "explanation": "", "learningObjectives": ["081.01.04.03.02"], + "explanation": "", "variants": { "aN0V4XKA": { - "id": "aN0V4XKA", "type": "simple", + "id": "aN0V4XKA", "question": "Which of these variables are required to calculate drag from the drag formula?", "options": [ { @@ -1036,12 +1036,12 @@ }, { "id": "Q0WGVBL2WF", - "explanation": "", "learningObjectives": ["081.01.01.05.08"], + "explanation": "", "variants": { "lV6cWp0Z": { - "id": "lV6cWp0Z", "type": "simple", + "id": "lV6cWp0Z", "question": "Reducing wing aspect ratio will", "options": [ { @@ -1077,12 +1077,12 @@ }, { "id": "Q0WJJTIRO7", - "explanation": "", "learningObjectives": ["081.01.04.02.03"], + "explanation": "", "variants": { "zvSF3ebC": { - "id": "zvSF3ebC", "type": "simple", + "id": "zvSF3ebC", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect? \nI Assuming no flow separation, the strength of wing tip vortices is not affected by angle of attack\nII The strength of wing tip vortices is not affected by aspect ratio.", "options": [ { @@ -1125,12 +1125,12 @@ }, { "id": "Q0XQ18MCHK", - "explanation": "", "learningObjectives": ["081.01.09.01.01"], + "explanation": "", "variants": { "iFX60oop": { - "id": "iFX60oop", "type": "simple", + "id": "iFX60oop", "question": "Refer to the image. \nWhich type of flap is shown in the figure?", "options": [ { @@ -1166,12 +1166,12 @@ }, { "id": "QQEARTX7H2", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "KPW45iC4": { - "id": "KPW45iC4", "type": "simple", + "id": "KPW45iC4", "question": "A flat plate, when positioned in the airflow at a small angle of attack, will produce:", "options": [ { @@ -1207,12 +1207,12 @@ }, { "id": "Q102J1PXI5", - "explanation": "", "learningObjectives": ["081.01.12.01.03"], + "explanation": "", "variants": { "hChZGJNl": { - "id": "hChZGJNl", "type": "simple", + "id": "hChZGJNl", "question": "While performing a take-off under icing conditions, the pilot rotates the aircraft at the correct speed and rate, but notices that the aircraft does NOT lift off as expected. What could be the cause?", "options": [ { @@ -1248,12 +1248,12 @@ }, { "id": "Q10UFYW2WO", - "explanation": "", "learningObjectives": ["081.01.05.07.02"], + "explanation": "", "variants": { "nS6aBOmh": { - "id": "nS6aBOmh", "type": "simple", + "id": "nS6aBOmh", "question": "Increasing air pressure will have the following effect on the drag of a body in an airstream (angle of attack, OAT and TAS are constant):", "options": [ { @@ -1289,12 +1289,12 @@ }, { "id": "Q304P7GQL9", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "d1AFt2ZK": { - "id": "d1AFt2ZK", "type": "simple", + "id": "d1AFt2ZK", "question": "When the lift coefficient CL of a symmetrical aerofoil section is zero, the pitching moment is:", "options": [ { @@ -1330,12 +1330,12 @@ }, { "id": "QUGVVA6ZOJ", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "ilr1NOyC": { - "id": "ilr1NOyC", "type": "simple", + "id": "ilr1NOyC", "question": "Regarding a positively cambered aerofoil section, which statement is correct?", "options": [ { @@ -1371,12 +1371,12 @@ }, { "id": "Q13DXUTMSD", - "explanation": "", "learningObjectives": ["081.01.01.04.07"], + "explanation": "", "variants": { "9psQOkQV": { - "id": "9psQOkQV", "type": "simple", + "id": "9psQOkQV", "question": "On a cambered airfoil the zero lift angle of attack will\nbe:", "options": [ { @@ -1412,12 +1412,12 @@ }, { "id": "Q141K7AEQ9", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "43lL5uWK": { - "id": "43lL5uWK", "type": "simple", + "id": "43lL5uWK", "question": "An aircraft climbs to FL210 with a CAS of 150 kt. Once reaching FL210 it accelerates to cruise speed whilst maintaining the same heading. What happens to the coefficient of lift?", "options": [ { @@ -1453,12 +1453,12 @@ }, { "id": "Q17EGWUNC9", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "eK2nIyhU": { - "id": "eK2nIyhU", "type": "simple", + "id": "eK2nIyhU", "question": "Induced drag is caused by:", "options": [ { @@ -1494,12 +1494,12 @@ }, { "id": "Q17SV0PW1H", - "explanation": "", "learningObjectives": ["081.01.06.04.02"], + "explanation": "", "variants": { "cndIBOR3": { - "id": "cndIBOR3", "type": "simple", + "id": "cndIBOR3", "question": "A large jet transport aeroplane has the following four flap positions: Up, Take-off, Approach and Landing and two slat positions: Retracted and Extended. Generally speaking, the selection that provides the highest positive contribution to C~LMAX~ is:", "options": [ { @@ -1540,12 +1540,12 @@ }, { "id": "Q182YV9IHA", - "explanation": "", "learningObjectives": ["081.01.01.02.01"], + "explanation": "", "variants": { "VbWvplDH": { - "id": "VbWvplDH", "type": "simple", + "id": "VbWvplDH", "question": "Select the correct statement in regard to a steady subsonic airflow.", "options": [ { @@ -1578,8 +1578,8 @@ "explanation": "" }, "np0RsjQA": { - "id": "np0RsjQA", "type": "simple", + "id": "np0RsjQA", "question": "Select the correct statement in regard to a steady subsonic airflow.", "options": [ { @@ -1612,8 +1612,8 @@ "explanation": "" }, "Hp9JuSIC": { - "id": "Hp9JuSIC", "type": "simple", + "id": "Hp9JuSIC", "question": "Select the correct statement in regard to a steady subsonic airflow.", "options": [ { @@ -1646,8 +1646,8 @@ "explanation": "" }, "2kwqCxCn": { - "id": "2kwqCxCn", "type": "simple", + "id": "2kwqCxCn", "question": "Select the correct statement in regards to a steady subsonic airflow.", "options": [ { @@ -1683,12 +1683,12 @@ }, { "id": "QPMD3KDCOV", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "Or91oidi": { - "id": "Or91oidi", "type": "simple", + "id": "Or91oidi", "question": "An aerofoil with positive camber at a positive angle of attack will have the highest flow velocity:", "options": [ { @@ -1724,12 +1724,12 @@ }, { "id": "Q191E57A4S", - "explanation": "", "learningObjectives": ["081.01.05.03.01"], + "explanation": "", "variants": { "XG1alVaW": { - "id": "XG1alVaW", "type": "simple", + "id": "XG1alVaW", "question": "What happens to parasite drag if the true airspeed of an aircraft is multiplied by two, and all other parameters are kept constant? The parasite drag..", "options": [ { @@ -1765,12 +1765,12 @@ }, { "id": "Q19N2Y0UL8", - "explanation": "", "learningObjectives": ["081.01.05.07.02"], + "explanation": "", "variants": { "vevPYfeN": { - "id": "vevPYfeN", "type": "simple", + "id": "vevPYfeN", "question": "At a given TAS, what effect will an increase in air density have on lift and drag?", "options": [ { @@ -1806,12 +1806,12 @@ }, { "id": "Q1A9TWJAVJ", - "explanation": "", "learningObjectives": ["081.01.04.03.03"], + "explanation": "", "variants": { "KYnZr2c1": { - "id": "KYnZr2c1", "type": "simple", + "id": "KYnZr2c1", "question": "Given a constant load factor, which of these statements is correct about the variation of induced drag with changes of speed and mass are correct or incorrect?\n\n1. When speed increases, induced drag decreases.2. When mass increases, induced drag decreases.", "options": [ { @@ -1856,12 +1856,12 @@ }, { "id": "QPRMP5RGE8", - "explanation": "", "learningObjectives": ["081.01.01.05.08"], + "explanation": "", "variants": { "Cz39bFJS": { - "id": "Cz39bFJS", "type": "simple", + "id": "Cz39bFJS", "question": "Decreasing the aspect ratio of a wing:", "options": [ { @@ -1902,8 +1902,8 @@ "explanation": "" }, "Vzopsdhu": { - "id": "Vzopsdhu", "type": "simple", + "id": "Vzopsdhu", "question": "Increasing the aspect ratio of a wing:", "options": [ { @@ -1939,12 +1939,12 @@ }, { "id": "Q1B49PW9EA", - "explanation": "", "learningObjectives": ["081.01", "081.03"], + "explanation": "", "variants": { "HOT4aGDO": { - "id": "HOT4aGDO", "type": "simple", + "id": "HOT4aGDO", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly increases the speed by 80 kt. Assuming the angle of attack remains constant, the load factor will initially:", "options": [ { @@ -2000,8 +2000,8 @@ "explanation": "" }, "52QfOd56": { - "id": "52QfOd56", "type": "simple", + "id": "52QfOd56", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly decreases the speed by 80 kt. Assuming the angle of attack remains constant, the load factor will initially:", "options": [ { @@ -2034,8 +2034,8 @@ "explanation": "" }, "aDcoSt3V": { - "id": "aDcoSt3V", "type": "simple", + "id": "aDcoSt3V", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly decreases the speed by 40 kt. Assuming the angle of attack remains constant, the load factor will initially:", "options": [ { @@ -2068,8 +2068,8 @@ "explanation": "" }, "6mRqAdIG": { - "id": "6mRqAdIG", "type": "simple", + "id": "6mRqAdIG", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly increases the speed by 40 kt. Assuming the angle of attack remains constant, the load factor will initially:", "options": [ { @@ -2102,8 +2102,8 @@ "explanation": "" }, "APDPcHeI": { - "id": "APDPcHeI", "type": "simple", + "id": "APDPcHeI", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly increases the speed by 60 kt. Assuming the angle of attack remains constant, the load factor will initially:", "options": [ { @@ -2136,8 +2136,8 @@ "explanation": "" }, "yNingJBf": { - "id": "yNingJBf", "type": "simple", + "id": "yNingJBf", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly decreases the speed by 60 kt. Assuming the angle of attack remains constant, the load factor will initially:", "options": [ { @@ -2170,8 +2170,8 @@ "explanation": "" }, "0fyvCdrV": { - "id": "0fyvCdrV", "type": "simple", + "id": "0fyvCdrV", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly increases the speed by 100 kt. Assuming the angle of attack remains constant, the load factor will initially:", "options": [ { @@ -2204,8 +2204,8 @@ "explanation": "" }, "V8V4gfBg": { - "id": "V8V4gfBg", "type": "simple", + "id": "V8V4gfBg", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly decreases the speed by 100 kt. Assuming the angle of attack remains constant, the load factor will initially:", "options": [ { @@ -2238,8 +2238,8 @@ "explanation": "" }, "4dXfI0J8": { - "id": "4dXfI0J8", "type": "simple", + "id": "4dXfI0J8", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly increases the speed by 20 kt. Assuming the angle of attack remains constant, the load factor will initially:", "options": [ { @@ -2272,8 +2272,8 @@ "explanation": "" }, "RWJVyZ2Y": { - "id": "RWJVyZ2Y", "type": "simple", + "id": "RWJVyZ2Y", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly decreases the speed by 20 kt. Assuming the angle of attack remains constant, the load factor will initially:", "options": [ { @@ -2306,8 +2306,8 @@ "explanation": "" }, "8k7jTjAe": { - "id": "8k7jTjAe", "type": "simple", + "id": "8k7jTjAe", "question": "An aeroplane flying at 100 kts in straight and level flight is subjected to a disturbance that suddenly increases the speed by 20 kts. Assuming the angle of attack remains constant, the load factor will initially:", "options": [ { @@ -2340,8 +2340,8 @@ "explanation": "" }, "r8ED0TP8": { - "id": "r8ED0TP8", "type": "simple", + "id": "r8ED0TP8", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly increases the speed by 10 kt. Assuming the angle of attack remains constant, the load factor will initially:", "options": [ { @@ -2374,8 +2374,8 @@ "explanation": "" }, "4WIroEgv": { - "id": "4WIroEgv", "type": "simple", + "id": "4WIroEgv", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly decreases the speed by 10 kt. Assuming the angle of attack remains constant, the load factor will initially:", "options": [ { @@ -2408,8 +2408,8 @@ "explanation": "" }, "mqGC8YS5": { - "id": "mqGC8YS5", "type": "simple", + "id": "mqGC8YS5", "question": "An aeroplane flying at 200 kts in straight and level flight is subjected to a disturbance that suddenly increases the speed by 10 kts. Assuming the angle of attack remains constant, the load factor will initially:", "options": [ { @@ -2445,12 +2445,12 @@ }, { "id": "Q1B6UFYO1L", - "explanation": "", "learningObjectives": ["081.01.01.05.08"], + "explanation": "", "variants": { "62xhMPgv": { - "id": "62xhMPgv", "type": "simple", + "id": "62xhMPgv", "question": "For a tapered wing the aspect ratio is?", "options": [ { @@ -2486,12 +2486,12 @@ }, { "id": "Q1BF6B69HA", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "2eDzRmLD": { - "id": "2eDzRmLD", "type": "simple", + "id": "2eDzRmLD", "question": "Refer to figure. \n What will be the consequence on the speed of the aircraft while going from Point B to Point C and maintaining steady, straight and level flight?", "options": [ { @@ -2527,12 +2527,12 @@ }, { "id": "Q1BPXCDBGQ", - "explanation": "", "learningObjectives": ["081.01.04.03.12"], + "explanation": "", "variants": { "b2WxTqpB": { - "id": "b2WxTqpB", "type": "simple", + "id": "b2WxTqpB", "question": "Refer to figure 081-47.\nSelect the airfoil profile that matches the corresponding C~L~ graph, i.e. which augmentation increases your C~L~ while your angle of attack remains the same?", "options": [ { @@ -2571,12 +2571,12 @@ }, { "id": "Q1CX1CEBJC", - "explanation": "", "learningObjectives": ["081.01.04.03.05"], + "explanation": "", "variants": { "Fo7Jwhix": { - "id": "Fo7Jwhix", "type": "simple", + "id": "Fo7Jwhix", "question": "Which wing configuration will experience a larger decrease in induced drag at heights between ground level and a wingspan?", "options": [ { @@ -2612,12 +2612,12 @@ }, { "id": "Q1D3CV4VNB", - "explanation": "", "learningObjectives": ["081.01.09.01.06"], + "explanation": "", "variants": { "Lvfj58wW": { - "id": "Lvfj58wW", "type": "simple", + "id": "Lvfj58wW", "question": "When Fowler type trailing edge flaps are extended at a constant angle of attack, the following changes will occur:", "options": [ { @@ -2656,8 +2656,8 @@ "explanation": "" }, "aUgbkjML": { - "id": "aUgbkjML", "type": "simple", + "id": "aUgbkjML", "question": "When Fowler type trailing edge flaps are extended at a constant angle of attack, the following changes will occur:", "options": [ { @@ -2693,12 +2693,12 @@ }, { "id": "Q8BBNR6EYP", - "explanation": "", "learningObjectives": ["081.01.03.02.01"], + "explanation": "", "variants": { "xMb4KyyT": { - "id": "xMb4KyyT", "type": "simple", + "id": "xMb4KyyT", "question": "Regarding the lift formula, if airspeed doubles, lift will:", "options": [ { @@ -2739,12 +2739,12 @@ }, { "id": "Q1FC7OTB3B", - "explanation": "", "learningObjectives": ["081.01.01.01.15"], + "explanation": "", "variants": { "vUTpXyCs": { - "id": "vUTpXyCs", "type": "simple", + "id": "vUTpXyCs", "question": "Which formula expresses the relationship between pressure, density, and absolute temperature of a given mass of air? The following mathematical symbols are used: p: pressure, rho: density, T: absolute temperature, x: multiplied by, / divided by:", "options": [ { @@ -2780,12 +2780,12 @@ }, { "id": "Q1FFWYQ6QY", - "explanation": "", "learningObjectives": ["081.01.05.07.02"], + "explanation": "", "variants": { "tosV5vFD": { - "id": "tosV5vFD", "type": "simple", + "id": "tosV5vFD", "question": "Increasing air density will have the following effect on the drag of a body in an airstream (angle of attack and TAS are constant):", "options": [ { @@ -2821,12 +2821,12 @@ }, { "id": "Q1GMQT4HTU", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "SR9qZvRC": { - "id": "SR9qZvRC", "type": "simple", + "id": "SR9qZvRC", "question": "Which of the following creates induced drag on a wing?", "options": [ { @@ -2862,12 +2862,12 @@ }, { "id": "Q1HBRJAW86", - "explanation": "", "learningObjectives": ["081.01.02.02.01"], + "explanation": "", "variants": { "UM6izjfC": { - "id": "UM6izjfC", "type": "simple", + "id": "UM6izjfC", "question": "Where do you expect the stagnation point to be on an aerofoil with high AOA?", "options": [ { @@ -2903,12 +2903,12 @@ }, { "id": "Q7507W6QP1", - "explanation": "", "learningObjectives": ["081.01.03.02.01"], + "explanation": "", "variants": { "y1Vb07ie": { - "id": "y1Vb07ie", "type": "simple", + "id": "y1Vb07ie", "question": "Select the option that lists the variables required for the lift formula.", "options": [ { @@ -2944,12 +2944,12 @@ }, { "id": "Q1IFFXG3DT", - "explanation": "", "learningObjectives": ["081.01.05.03.01"], + "explanation": "", "variants": { "f0GUSa18": { - "id": "f0GUSa18", "type": "simple", + "id": "f0GUSa18", "question": "A body is placed within an airstream. If the density of the airstream decreases to half its original value, the parasite drag will decrease by a factor of...", "options": [ { @@ -2990,12 +2990,12 @@ }, { "id": "Q1NF5PFZZ3", - "explanation": "", "learningObjectives": ["081.01.01.04.03"], + "explanation": "", "variants": { "uS2dPiPM": { - "id": "uS2dPiPM", "type": "simple", + "id": "uS2dPiPM", "question": "The angle between the direction of the undisturbed airflow (relative wind) and the chord line of an aerofoil is the:", "options": [ { @@ -3036,12 +3036,12 @@ }, { "id": "Q1NSSP1WJQ", - "explanation": "", "learningObjectives": ["081.01.01.03.08"], + "explanation": "", "variants": { "GtLqwLwZ": { - "id": "GtLqwLwZ", "type": "simple", + "id": "GtLqwLwZ", "question": "The induced angle of attack is", "options": [ { @@ -3083,12 +3083,12 @@ }, { "id": "Q1PSSRHLCZ", - "explanation": "", "learningObjectives": ["081.01.01.05.11"], + "explanation": "", "variants": { "BHVQWCLt": { - "id": "BHVQWCLt", "type": "simple", + "id": "BHVQWCLt", "question": "Wing twist (geometric and aerodynamic) is used to:\n\n1. improve stall characteristics.2. reduce induced drag.3. reduce interference drag.4. increase VMO.\nThe combination that regroups all of the correct statements is:\n ", "options": [ { @@ -3129,12 +3129,12 @@ }, { "id": "QMXDUH924P", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "qv2ZoMAX": { - "id": "qv2ZoMAX", "type": "simple", + "id": "qv2ZoMAX", "question": "Which is the correct statement for induced drag at a constant load factor?", "options": [ { @@ -3170,12 +3170,12 @@ }, { "id": "QP0SAG06VW", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "XZTFEL5m": { - "id": "XZTFEL5m", "type": "simple", + "id": "XZTFEL5m", "question": "If the lift generated by a given wing is 1000 kN, what will be the lift if the wing area is doubled?", "options": [ { @@ -3211,12 +3211,12 @@ }, { "id": "QHPCYPGT55", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "OKTfIhv5": { - "id": "OKTfIhv5", "type": "simple", + "id": "OKTfIhv5", "question": "Which part of the aeroplane has the largest effect on induced drag?", "options": [ { @@ -3257,12 +3257,12 @@ }, { "id": "Q1RNJXWO57", - "explanation": "", "learningObjectives": ["081.01.04.02.03"], + "explanation": "", "variants": { "976SyEGi": { - "id": "976SyEGi", "type": "simple", + "id": "976SyEGi", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices decreases as the angle of attack increases.\n2) The strength of wing tip vortices decreases as the aspect ratio decreases.", "options": [ { @@ -3314,8 +3314,8 @@ "explanation": "" }, "5hbN3JMM": { - "id": "5hbN3JMM", "type": "simple", + "id": "5hbN3JMM", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices decreases as the angle of attack decreases.\n2) The strength of wing tip vortices increases as the aspect ratio decreases.", "options": [ { @@ -3348,8 +3348,8 @@ "explanation": "" }, "9ZgDMsLw": { - "id": "9ZgDMsLw", "type": "simple", + "id": "9ZgDMsLw", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack decreases.\n2) The strength of wing tip vortices decreases as the aspect ratio decreases.", "options": [ { @@ -3382,8 +3382,8 @@ "explanation": "" }, "tLWhwqWw": { - "id": "tLWhwqWw", "type": "simple", + "id": "tLWhwqWw", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices decreases as the angle of attack decreases.\n2) The strength of wing tip vortices decreases as the aspect ratio increases.", "options": [ { @@ -3416,8 +3416,8 @@ "explanation": "" }, "0IGuQ8xu": { - "id": "0IGuQ8xu", "type": "simple", + "id": "0IGuQ8xu", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices decreases as the angle of attack decreases.\n2) The strength of wing tip vortices decreases as the aspect ratio decreases.", "options": [ { @@ -3450,8 +3450,8 @@ "explanation": "" }, "gRYnfb8P": { - "id": "gRYnfb8P", "type": "simple", + "id": "gRYnfb8P", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack decreases.\n2) The strength of wing tip vortices increases as the aspect ratio increases.", "options": [ { @@ -3484,8 +3484,8 @@ "explanation": "" }, "3iriW0O1": { - "id": "3iriW0O1", "type": "simple", + "id": "3iriW0O1", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack increases.\n2) The strength of wing tip vortices decreases as the aspect ratio increases.", "options": [ { @@ -3518,8 +3518,8 @@ "explanation": "" }, "HE093QWC": { - "id": "HE093QWC", "type": "simple", + "id": "HE093QWC", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices decreases as the angle of attack increases.\n2) The strength of wing tip vortices increases as the aspect ratio increases.", "options": [ { @@ -3552,8 +3552,8 @@ "explanation": "" }, "YuHitHve": { - "id": "YuHitHve", "type": "simple", + "id": "YuHitHve", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack increases.\n2) The strength of wing tip vortices increases as the aspect ratio decreases.", "options": [ { @@ -3586,8 +3586,8 @@ "explanation": "" }, "wZHPAKqd": { - "id": "wZHPAKqd", "type": "simple", + "id": "wZHPAKqd", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack increases.\n2) The strength of wing tip vortices increases as the aspect ratio increases.", "options": [ { @@ -3620,8 +3620,8 @@ "explanation": "" }, "H1RXOvY9": { - "id": "H1RXOvY9", "type": "simple", + "id": "H1RXOvY9", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices decreases as the angle of attack increases.\n2) The strength of wing tip vortices decreases as the aspect ratio increases.", "options": [ { @@ -3654,8 +3654,8 @@ "explanation": "" }, "7z9Z01gH": { - "id": "7z9Z01gH", "type": "simple", + "id": "7z9Z01gH", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack decreases.\n2) The strength of wing tip vortices decreases as the aspect ratio increases.", "options": [ { @@ -3688,8 +3688,8 @@ "explanation": "" }, "yIilBrgx": { - "id": "yIilBrgx", "type": "simple", + "id": "yIilBrgx", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices decreases as the angle of attack decreases.\n2) The strength of wing tip vortices increases as the aspect ratio increases.", "options": [ { @@ -3722,8 +3722,8 @@ "explanation": "" }, "kd2Nz7oY": { - "id": "kd2Nz7oY", "type": "simple", + "id": "kd2Nz7oY", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices decreases as the angle of attack increases.\n2) The strength of wing tip vortices increases as the aspect ratio decreases.", "options": [ { @@ -3756,8 +3756,8 @@ "explanation": "" }, "zGvy2sWG": { - "id": "zGvy2sWG", "type": "simple", + "id": "zGvy2sWG", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack decreases.\n2) The strength of wing tip vortices increases as the aspect ratio decreases.", "options": [ { @@ -3790,8 +3790,8 @@ "explanation": "" }, "E4mcJMse": { - "id": "E4mcJMse", "type": "simple", + "id": "E4mcJMse", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack increases.\n2) The strength of wing tip vortices decreases as the aspect ratio decreases.", "options": [ { @@ -3827,12 +3827,12 @@ }, { "id": "Q1UFYVLEEF", - "explanation": "", "learningObjectives": ["081.01.05.01.01"], + "explanation": "", "variants": { "0Y8ii0pV": { - "id": "0Y8ii0pV", "type": "simple", + "id": "0Y8ii0pV", "question": "Which statements, about the effects on drag of removing external tip tanks from the wings of an aeroplane are correct or incorrect?\n1) Parasite drag increases.\n2) Induced drag increases.", "options": [ { @@ -3871,8 +3871,8 @@ "explanation": "" }, "P7AwrZPO": { - "id": "P7AwrZPO", "type": "simple", + "id": "P7AwrZPO", "question": "Which statements, about the effects on drag of removing external tip tanks from the wings of an aeroplane are correct or incorrect?\n1) Parasite drag increases.\n2) Induced drag decreases.", "options": [ { @@ -3905,8 +3905,8 @@ "explanation": "" }, "Y3fCa3Zd": { - "id": "Y3fCa3Zd", "type": "simple", + "id": "Y3fCa3Zd", "question": "Which statements, about the effects on drag of removing external tip tanks from the wings of an aeroplane are correct or incorrect?\n1) Parasite drag decreases.\n2) Induced drag increases.", "options": [ { @@ -3942,12 +3942,12 @@ }, { "id": "Q1UTWVICCM", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "iBHPMpsx": { - "id": "iBHPMpsx", "type": "simple", + "id": "iBHPMpsx", "question": "At a load factor of 1 and the aeroplane’s minimum drag speed, what is the ratio between induced drag Di and parasite drag Dp?", "options": [ { @@ -3983,12 +3983,12 @@ }, { "id": "Q1VO7KOUXB", - "explanation": "", "learningObjectives": ["081.01.03.03.02"], + "explanation": "", "variants": { "VnDBorNU": { - "id": "VnDBorNU", "type": "simple", + "id": "VnDBorNU", "question": "Refer to figure 081-10.\nWhich one of the bodies in motion (all bodies have the same cross section area) will have the least form drag?", "options": [ { @@ -4024,8 +4024,8 @@ "explanation": "" }, "qpmf0aUl": { - "id": "qpmf0aUl", "type": "simple", + "id": "qpmf0aUl", "question": "Refer to figure 081-10.\nWhich one of the bodies in motion (all bodies have the same cross section area) will have the highest form drag?", "options": [ { @@ -4061,12 +4061,12 @@ }, { "id": "Q1XBBLMJ3R", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "XSfWuN2p": { - "id": "XSfWuN2p", "type": "simple", + "id": "XSfWuN2p", "question": "What is the effect on induced drag of an increase in aspect ratio?", "options": [ { @@ -4107,12 +4107,12 @@ }, { "id": "Q1ZCXDK77G", - "explanation": "", "learningObjectives": ["081.01.02.01.02"], + "explanation": "", "variants": { "DnOl1wrn": { - "id": "DnOl1wrn", "type": "simple", + "id": "DnOl1wrn", "question": "Which of these statements about a steady subsonic flow are correct or incorrect?\n1) The static pressure decreases as the streamlines converge.\n2) The velocity increases as the streamlines converge.", "options": [ { @@ -4155,12 +4155,12 @@ }, { "id": "Q22XP1IF4D", - "explanation": "", "learningObjectives": ["081.01.04.03.03"], + "explanation": "", "variants": { "PrvtTrZW": { - "id": "PrvtTrZW", "type": "simple", + "id": "PrvtTrZW", "question": "If the airspeed reduces in level flight below the speed for maximum L/D, the total drag of an aeroplane will", "options": [ { @@ -4201,12 +4201,12 @@ }, { "id": "Q23R0H40I9", - "explanation": "", "learningObjectives": ["081.01.04.03.12"], + "explanation": "", "variants": { "5JvGnSzp": { - "id": "5JvGnSzp", "type": "simple", + "id": "5JvGnSzp", "question": "Which of the following configurations of an airplane give the highest value of the C~L~/C~D~ ratio?", "options": [ { @@ -4242,12 +4242,12 @@ }, { "id": "Q23XFODH04", - "explanation": "", "learningObjectives": ["081.01.02.02.01"], + "explanation": "", "variants": { "yQ7RW7Rt": { - "id": "yQ7RW7Rt", "type": "simple", + "id": "yQ7RW7Rt", "question": "The stagnation point is the point", "options": [ { @@ -4288,12 +4288,12 @@ }, { "id": "Q28IV8ERT7", - "explanation": "", "learningObjectives": ["081.01.01.01.11"], + "explanation": "", "variants": { "GQgLFh8M": { - "id": "GQgLFh8M", "type": "simple", + "id": "GQgLFh8M", "question": "Which of these statements about Bernoulli equation is correct?", "options": [ { @@ -4329,12 +4329,12 @@ }, { "id": "QJ1PBZ7ZXA", - "explanation": "", "learningObjectives": ["081.01.04.03.02"], + "explanation": "", "variants": { "bh2BkAWp": { - "id": "bh2BkAWp", "type": "simple", + "id": "bh2BkAWp", "question": "The coefficient of drag can be defined as the..", "options": [ { @@ -4370,12 +4370,12 @@ }, { "id": "QEQD696DXJ", - "explanation": "", "learningObjectives": ["081.01.01.03.05"], + "explanation": "", "variants": { "4oN1cmgQ": { - "id": "4oN1cmgQ", "type": "simple", + "id": "4oN1cmgQ", "question": "The aerodynamic drag of a body, placed in a certain airstream depends amongst others on:", "options": [ { @@ -4416,12 +4416,12 @@ }, { "id": "Q29QMFX9CB", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "LPM1GWQm": { - "id": "LPM1GWQm", "type": "simple", + "id": "LPM1GWQm", "question": "The lift and drag forces, acting on an aerofoil:", "options": [ { @@ -4462,12 +4462,12 @@ }, { "id": "Q29W5Q2HPN", - "explanation": "", "learningObjectives": ["081.01.04.03.03"], + "explanation": "", "variants": { "x28khNqh": { - "id": "x28khNqh", "type": "simple", + "id": "x28khNqh", "question": "In what way do (1) induced drag and (2) parasite drag alter with increasing speed in straight and level flight?", "options": [ { @@ -4503,12 +4503,12 @@ }, { "id": "Q2AAPFBH0A", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "9sp9EOSV": { - "id": "9sp9EOSV", "type": "simple", + "id": "9sp9EOSV", "question": "Comparing the lift coefficient and drag coefficient for conventional aeroplanes", "options": [ { @@ -4544,12 +4544,12 @@ }, { "id": "QTOLGM8TR6", - "explanation": "", "learningObjectives": ["081.01.04.02.07"], + "explanation": "", "variants": { "17jloR8t": { - "id": "17jloR8t", "type": "simple", + "id": "17jloR8t", "question": "The intensity or strength of the wing-tip vortices is..", "options": [ { @@ -4590,12 +4590,12 @@ }, { "id": "Q2B9M7K3BD", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "6bXppZM3": { - "id": "6bXppZM3", "type": "simple", + "id": "6bXppZM3", "question": "Induced drag is created by the", "options": [ { @@ -4636,12 +4636,12 @@ }, { "id": "Q2BHHHZV4J", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "KDlX5ww2": { - "id": "KDlX5ww2", "type": "simple", + "id": "KDlX5ww2", "question": "An aeroplane entering the ground effect during the landing phase will experience", "options": [ { @@ -4677,12 +4677,12 @@ }, { "id": "Q2C7JT1SO1", - "explanation": "", "learningObjectives": ["081.01.01.05.08"], + "explanation": "", "variants": { "IyliknxO": { - "id": "IyliknxO", "type": "simple", + "id": "IyliknxO", "question": "Aspect ratio of a wing is the ratio between:", "options": [ { @@ -4715,8 +4715,8 @@ "explanation": "" }, "TCNVEpqw": { - "id": "TCNVEpqw", "type": "simple", + "id": "TCNVEpqw", "question": "Aspect ratio of a wing is the ratio between:", "options": [ { @@ -4749,8 +4749,8 @@ "explanation": "" }, "sBFFRb23": { - "id": "sBFFRb23", "type": "simple", + "id": "sBFFRb23", "question": "Aspect ratio of a wing is the ratio between:", "options": [ { @@ -4786,12 +4786,12 @@ }, { "id": "Q2CJV914IW", - "explanation": "", "learningObjectives": ["081.01.05.01.01"], + "explanation": "", "variants": { "Xz0VDUiX": { - "id": "Xz0VDUiX", "type": "simple", + "id": "Xz0VDUiX", "question": "Which statement, about the effects on drag of removing external tip tanks from the wings of an aeroplane, is correct?\n\n1. Parasite drag increases.\n\n2. Induced drag decreases.", "options": [ { @@ -4836,8 +4836,8 @@ "explanation": "" }, "GltjDPFJ": { - "id": "GltjDPFJ", "type": "simple", + "id": "GltjDPFJ", "question": "Which statement, about the effects on drag of removing external tip tanks from the wings of an aeroplane, is correct?\n\n1. Parasite drag decreases.\n\n2. Induced drag increases.", "options": [ { @@ -4870,8 +4870,8 @@ "explanation": "" }, "0EyeeH5K": { - "id": "0EyeeH5K", "type": "simple", + "id": "0EyeeH5K", "question": "Which statement, about the effects on drag of removing external tip tanks from the wings of an aeroplane, is correct?\n\n1. Parasite drag increases.\n\n2. Induced drag increases.", "options": [ { @@ -4904,8 +4904,8 @@ "explanation": "" }, "5tN5JugL": { - "id": "5tN5JugL", "type": "simple", + "id": "5tN5JugL", "question": "Which statement, about the effects on drag of removing external tip tanks from the wings of an aeroplane, is correct?\n\n1. Parasite drag decreases.\n\n2. Induced drag decreases.", "options": [ { @@ -4941,12 +4941,12 @@ }, { "id": "Q2DFB0VHBH", - "explanation": "", "learningObjectives": ["081.01.06.01.03"], + "explanation": "", "variants": { "Tt5aye19": { - "id": "Tt5aye19", "type": "simple", + "id": "Tt5aye19", "question": "When an aeroplane enters ground effect:", "options": [ { @@ -4984,8 +4984,8 @@ "explanation": "" }, "j66qJPwC": { - "id": "j66qJPwC", "type": "simple", + "id": "j66qJPwC", "question": "When an aeroplane enters ground effect:", "options": [ { @@ -5021,12 +5021,12 @@ }, { "id": "Q2FG5271WF", - "explanation": "", "learningObjectives": ["081.01.04.03.12"], + "explanation": "", "variants": { "IbSkHUvv": { - "id": "IbSkHUvv", "type": "simple", + "id": "IbSkHUvv", "question": "The Parasite Drag formula is : Parasite Drag = Cdp x (½rhoV²) x S. In low subsonic flight, the Parasite Drag Coefficient (Cdp) is determined by:", "options": [ { @@ -5062,12 +5062,12 @@ }, { "id": "Q2FUKIQZ5V", - "explanation": "", "learningObjectives": ["081.01.01.03.08"], + "explanation": "", "variants": { "Gzbsj5gY": { - "id": "Gzbsj5gY", "type": "simple", + "id": "Gzbsj5gY", "question": "The angle of attack of an airfoil profile is defined as the angle between:", "options": [ { @@ -5100,8 +5100,8 @@ "explanation": "" }, "G5UdTsVb": { - "id": "G5UdTsVb", "type": "simple", + "id": "G5UdTsVb", "question": "The angle of attack of an airfoil profile is defined as the angle between:", "options": [ { @@ -5137,12 +5137,12 @@ }, { "id": "QLVTCVPKZU", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "EktwBFGc": { - "id": "EktwBFGc", "type": "simple", + "id": "EktwBFGc", "question": "Whilst maintaining straight and level flight with a lift coefficient CL = 1 what will be the new approximate value of CL after the speed is increased by 30 %?", "options": [ { @@ -5175,8 +5175,8 @@ "explanation": "" }, "eVy2chIq": { - "id": "eVy2chIq", "type": "simple", + "id": "eVy2chIq", "question": "Whilst maintaining straight and level flight with a lift coefficient CL = 1 what will be the new approximate value of CL after the speed is increased by 30%?", "options": [ { @@ -5212,12 +5212,12 @@ }, { "id": "Q2IIDSEXH1", - "explanation": "", "learningObjectives": ["081.01.01.04.07"], + "explanation": "", "variants": { "ONmpozDk": { - "id": "ONmpozDk", "type": "simple", + "id": "ONmpozDk", "question": "The angle of attack of an aerofoil section is the angle between the", "options": [ { @@ -5253,12 +5253,12 @@ }, { "id": "Q2ILI216U1", - "explanation": "", "learningObjectives": ["081.01.01.04.01"], + "explanation": "", "variants": { "h2ZsAkUe": { - "id": "h2ZsAkUe", "type": "simple", + "id": "h2ZsAkUe", "question": "While increasing the angle of attack, the leading edge stagnation point of the aerofoil moves towards the...", "options": [ { @@ -5294,12 +5294,12 @@ }, { "id": "Q2KUG2CHXD", - "explanation": "", "learningObjectives": ["081.01.01.04.07"], + "explanation": "", "variants": { "kl561bZJ": { - "id": "kl561bZJ", "type": "simple", + "id": "kl561bZJ", "question": "An aerofoil is cambered when:", "options": [ { @@ -5340,12 +5340,12 @@ }, { "id": "Q2MQUOEVYJ", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "X2a6aZWX": { - "id": "X2a6aZWX", "type": "simple", + "id": "X2a6aZWX", "question": "During a flight when the trailing edge flaps are lowered to the fully extended position:", "options": [ { @@ -5378,8 +5378,8 @@ "explanation": "" }, "swZbc61T": { - "id": "swZbc61T", "type": "simple", + "id": "swZbc61T", "question": "During a flight when the trailing edge flaps are lowered to the fully extended position:", "options": [ { @@ -5415,12 +5415,12 @@ }, { "id": "Q2MY69CZ84", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "cN85FlRZ": { - "id": "cN85FlRZ", "type": "simple", + "id": "cN85FlRZ", "question": "What happens to velocity and lift when you decrease the angle of attack?", "options": [ { @@ -5456,12 +5456,12 @@ }, { "id": "Q2N4F976PO", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "VKJI5H9M": { - "id": "VKJI5H9M", "type": "simple", + "id": "VKJI5H9M", "question": "As speed is reduced in level flight CL will....(1)....\nand alpha will....(2)....", "options": [ { @@ -5497,12 +5497,12 @@ }, { "id": "Q2TOA6WLLX", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "9xHKbrov": { - "id": "9xHKbrov", "type": "simple", + "id": "9xHKbrov", "question": "Which of the following statements about the difference between Krueger flaps and slats is correct?", "options": [ { @@ -5535,8 +5535,8 @@ "explanation": "" }, "OBERwBzN": { - "id": "OBERwBzN", "type": "simple", + "id": "OBERwBzN", "question": "Which of the following statements about the difference between Krueger flaps and slats is correct?", "options": [ { @@ -5572,12 +5572,12 @@ }, { "id": "Q2V6ROJK4D", - "explanation": "", "learningObjectives": ["081.01.06.01.03"], + "explanation": "", "variants": { "IgvLIwnl": { - "id": "IgvLIwnl", "type": "simple", + "id": "IgvLIwnl", "question": "Which of the following statements is true regarding ground effect?", "options": [ { @@ -5613,12 +5613,12 @@ }, { "id": "Q2WO9WE9KP", - "explanation": "", "learningObjectives": ["081.01.09.02.03"], + "explanation": "", "variants": { "9Eg60M4I": { - "id": "9Eg60M4I", "type": "simple", + "id": "9Eg60M4I", "question": "When trailing edge flaps are deployed, camber is changed at the back of the aerofoil and:", "options": [ { @@ -5654,12 +5654,12 @@ }, { "id": "Q2YBI3M7KU", - "explanation": "", "learningObjectives": ["081.01.01.05.06"], + "explanation": "", "variants": { "NW4rnFhn": { - "id": "NW4rnFhn", "type": "simple", + "id": "NW4rnFhn", "question": "The mean geometric chord of a wing is the..", "options": [ { @@ -5700,12 +5700,12 @@ }, { "id": "Q2ZSF5IRUK", - "explanation": "", "learningObjectives": ["081.01", "081.03", "081.08"], + "explanation": "", "variants": { "mpOcOZjd": { - "id": "mpOcOZjd", "type": "simple", + "id": "mpOcOZjd", "question": "Dividing lift by weight gives:", "options": [ { @@ -5746,12 +5746,12 @@ }, { "id": "Q31YNNYHMI", - "explanation": "", "learningObjectives": ["081.01.09.01.05"], + "explanation": "", "variants": { "CpAmgror": { - "id": "CpAmgror", "type": "simple", + "id": "CpAmgror", "question": "A slotted flap will increase the CLMAX by:", "options": [ { @@ -5792,12 +5792,12 @@ }, { "id": "Q32MWPV1QM", - "explanation": "", "learningObjectives": ["081.01", "081.08"], + "explanation": "", "variants": { "c0zlG4mV": { - "id": "c0zlG4mV", "type": "simple", + "id": "c0zlG4mV", "question": "How does high airfield elevation affect Vmcg?", "options": [ { @@ -5833,12 +5833,12 @@ }, { "id": "Q32SOFWFSN", - "explanation": "", "learningObjectives": ["081.01.03.02.01"], + "explanation": "", "variants": { "Ef8lMFgp": { - "id": "Ef8lMFgp", "type": "simple", + "id": "Ef8lMFgp", "question": "Regarding the lift formula, if density doubles, lift will:", "options": [ { @@ -5874,12 +5874,12 @@ }, { "id": "Q37HXQCN5W", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "zdVlHHeU": { - "id": "zdVlHHeU", "type": "simple", + "id": "zdVlHHeU", "question": "Which of the following statements about drag and lift is correct?", "options": [ { @@ -5915,12 +5915,12 @@ }, { "id": "QCY2NQL3HE", - "explanation": "", "learningObjectives": ["081.01.06.01.03"], + "explanation": "", "variants": { "v4mF5Efn": { - "id": "v4mF5Efn", "type": "simple", + "id": "v4mF5Efn", "question": "Assuming constant IAS, when an aeroplane leaves ground effect:", "options": [ { @@ -5971,8 +5971,8 @@ "explanation": "" }, "t8SzzPug": { - "id": "t8SzzPug", "type": "simple", + "id": "t8SzzPug", "question": "Assuming constant IAS, when an aeroplane leaves ground effect:", "options": [ { @@ -6005,8 +6005,8 @@ "explanation": "" }, "Aed4Jc5O": { - "id": "Aed4Jc5O", "type": "simple", + "id": "Aed4Jc5O", "question": "Assuming constant IAS, when an aeroplane leaves ground effect:", "options": [ { @@ -6039,8 +6039,8 @@ "explanation": "" }, "DKOf8KWV": { - "id": "DKOf8KWV", "type": "simple", + "id": "DKOf8KWV", "question": "Assuming constant IAS, when an aeroplane leaves ground effect:", "options": [ { @@ -6076,12 +6076,12 @@ }, { "id": "Q38I66HUML", - "explanation": "", "learningObjectives": ["081.01.09.01.09"], + "explanation": "", "variants": { "OA1LMn5R": { - "id": "OA1LMn5R", "type": "simple", + "id": "OA1LMn5R", "question": "In the initial climb after take-off, flaps are accidentally retracted prematurely. The effect might be:", "options": [ { @@ -6117,12 +6117,12 @@ }, { "id": "Q38XFGALN8", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "7TnKxUcE": { - "id": "7TnKxUcE", "type": "simple", + "id": "7TnKxUcE", "question": "The Lift Coefficient versus Angle Of Attack curve of a negatively cambered aerofoil section intersects the vertical axis of the graph", "options": [ { @@ -6161,8 +6161,8 @@ "explanation": "" }, "4CDJNxNq": { - "id": "4CDJNxNq", "type": "simple", + "id": "4CDJNxNq", "question": "The Lift Coefficient versus Angle Of Attack curve of a negatively cambered aerofoil section intersects the horizontal axis of the graph", "options": [ { @@ -6195,8 +6195,8 @@ "explanation": "" }, "0Rhv42sz": { - "id": "0Rhv42sz", "type": "simple", + "id": "0Rhv42sz", "question": "The Lift Coefficient versus Angle Of Attack curve of a positively cambered aerofoil section intersects the horizontal axis of the graph", "options": [ { @@ -6229,8 +6229,8 @@ "explanation": "" }, "J3OuSpro": { - "id": "J3OuSpro", "type": "simple", + "id": "J3OuSpro", "question": "The Lift Coefficient versus Angle Of Attack curve of a symmetrical aerofoil section intersects the vertical axis of the graph", "options": [ { @@ -6266,12 +6266,12 @@ }, { "id": "Q3A4ISOTI8", - "explanation": "", "learningObjectives": ["081.01.05.03.01"], + "explanation": "", "variants": { "sfOJSO2L": { - "id": "sfOJSO2L", "type": "simple", + "id": "sfOJSO2L", "question": "The value of the parasite drag in straight and level flight at constant weight varies linearly with the:", "options": [ { @@ -6312,12 +6312,12 @@ }, { "id": "Q3BT6DPEWS", - "explanation": "", "learningObjectives": ["081.01.04.03.04"], + "explanation": "", "variants": { "D4a0fGHt": { - "id": "D4a0fGHt", "type": "simple", + "id": "D4a0fGHt", "question": "Which statement about induced drag is correct?\n\nI. Induced drag increases as angle of attack increases. \n II. At constant load factor, induced drag decreases with increasing aeroplane mass.", "options": [ { @@ -6360,12 +6360,12 @@ }, { "id": "Q3BWODDRYI", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "9wsXTZni": { - "id": "9wsXTZni", "type": "simple", + "id": "9wsXTZni", "question": "Extension of leading edge flaps will:", "options": [ { @@ -6403,8 +6403,8 @@ "explanation": "" }, "2Bt5Rkpd": { - "id": "2Bt5Rkpd", "type": "simple", + "id": "2Bt5Rkpd", "question": "Extension of leading edge flaps will:", "options": [ { @@ -6440,12 +6440,12 @@ }, { "id": "Q3C93T6FWG", - "explanation": "", "learningObjectives": ["081.01.12.01.03"], + "explanation": "", "variants": { "p0LhWZsp": { - "id": "p0LhWZsp", "type": "simple", + "id": "p0LhWZsp", "question": "If you are landing on a warm summer’s day, the increased temperature of the runway will:", "options": [ { @@ -6481,12 +6481,12 @@ }, { "id": "Q3CK1IQGKU", - "explanation": "", "learningObjectives": ["081.01", "081.03"], + "explanation": "", "variants": { "IcpekQ2m": { - "id": "IcpekQ2m", "type": "simple", + "id": "IcpekQ2m", "question": "Which boundary layer, when considering its velocity profile perpendicular to the flow, has the greatest change in velocity close to the surface?", "options": [ { @@ -6527,12 +6527,12 @@ }, { "id": "Q3DBJRR1GO", - "explanation": "", "learningObjectives": ["081.01.09.02.07"], + "explanation": "", "variants": { "m6s0UF4D": { - "id": "m6s0UF4D", "type": "simple", + "id": "m6s0UF4D", "question": "The difference between the effects of slat and flap asymmetry is that: (large in the context of this question means not or hardly controllable by normal use of controls)", "options": [ { @@ -6573,12 +6573,12 @@ }, { "id": "Q3EHMXNTEG", - "explanation": "", "learningObjectives": ["081.01.01.03.08"], + "explanation": "", "variants": { "us29D1uP": { - "id": "us29D1uP", "type": "simple", + "id": "us29D1uP", "question": "Which statement is correct regarding the Lift Coefficient and Angle Of Attack?", "options": [ { @@ -6614,12 +6614,12 @@ }, { "id": "Q3GEBPZ5VD", - "explanation": "", "learningObjectives": ["081.01.05.02.02"], + "explanation": "", "variants": { "FpLw0dkw": { - "id": "FpLw0dkw", "type": "simple", + "id": "FpLw0dkw", "question": "An aeroplane is being fitted and certified to carry an external piece of scientific equipment, which will increase drag. Which of the following factors will minimise the increase in form (pressure) drag?", "options": [ { @@ -6655,12 +6655,12 @@ }, { "id": "Q3GLDILZQA", - "explanation": "", "learningObjectives": ["081.01.04.03.12"], + "explanation": "", "variants": { "jsea42X6": { - "id": "jsea42X6", "type": "simple", + "id": "jsea42X6", "question": "An airplane flying at 100 kt at an angle (alpha 1) of 4 degrees, has a drag coefficient (C~D1~) of 0.028. Total drag force is 900 N.\n \nThe airplane decelerates to 55 kt, flying at an angle of attack (alpha 2) of 15 degrees, when drag coefficient (C~D2~) is 0.148.\n \nWhat is the new value of the drag force?", "options": [ { @@ -6696,12 +6696,12 @@ }, { "id": "Q3IGZS7MFO", - "explanation": "", "learningObjectives": ["081.01.04.03.03"], + "explanation": "", "variants": { "UKMdKy2U": { - "id": "UKMdKy2U", "type": "simple", + "id": "UKMdKy2U", "question": "What happens to induced drag when airspeed increases?", "options": [ { @@ -6737,12 +6737,12 @@ }, { "id": "QGG9L3L4HN", - "explanation": "", "learningObjectives": ["081.01.09.02.07"], + "explanation": "", "variants": { "wZAGZFKM": { - "id": "wZAGZFKM", "type": "simple", + "id": "wZAGZFKM", "question": "Slat or flap asymmetry occurring after either extension or retraction, may have an effect on controllability since:", "options": [ { @@ -6783,12 +6783,12 @@ }, { "id": "Q3PYAE3S3Y", - "explanation": "", "learningObjectives": ["081.01.04.03.03"], + "explanation": "", "variants": { "nt8ywdrn": { - "id": "nt8ywdrn", "type": "simple", + "id": "nt8ywdrn", "question": "In what way do I. induced drag and II. parasite drag alter with increasing speed in straight and level flight?", "options": [ { @@ -6824,12 +6824,12 @@ }, { "id": "QM34OM3TJH", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "4XrsjLr2": { - "id": "4XrsjLr2", "type": "simple", + "id": "4XrsjLr2", "question": "The lift force, acting on an aerofoil: (no flow separation)", "options": [ { @@ -6865,12 +6865,12 @@ }, { "id": "Q3RRGFZNVW", - "explanation": "", "learningObjectives": ["081.01.04.03.05"], + "explanation": "", "variants": { "uyWGe6Nn": { - "id": "uyWGe6Nn", "type": "simple", + "id": "uyWGe6Nn", "question": "Which of the following wing planforms produces the lowest induced drag? (assume zero wing twist)", "options": [ { @@ -6908,8 +6908,8 @@ "explanation": "" }, "9WV5Sa4h": { - "id": "9WV5Sa4h", "type": "simple", + "id": "9WV5Sa4h", "question": "Which of the following wing planforms produces the lowest induced drag? (assume zero wing twist)", "options": [ { @@ -6945,12 +6945,12 @@ }, { "id": "Q3THUGZQ9N", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "3nolAZdz": { - "id": "3nolAZdz", "type": "simple", + "id": "3nolAZdz", "question": "Consider the resultant force caused by pressure distribution around an aerofoil moving through the air, its originating point is the (1)___ and its direction forms a(n) (2)___ angle with the relative air flow.", "options": [ { @@ -6986,12 +6986,12 @@ }, { "id": "Q3VCBIJLUE", - "explanation": "", "learningObjectives": ["081.01.01.01.03"], + "explanation": "", "variants": { "Ai79QX7m": { - "id": "Ai79QX7m", "type": "simple", + "id": "Ai79QX7m", "question": "'A body will continue at rest or in a state of uniform\nmotion unless acted on by an external force'. This is:", "options": [ { @@ -7027,12 +7027,12 @@ }, { "id": "Q3Y0I3UKGX", - "explanation": "", "learningObjectives": ["081.01.09.02.03"], + "explanation": "", "variants": { "z3ayQIWu": { - "id": "z3ayQIWu", "type": "simple", + "id": "z3ayQIWu", "question": "On a wing fitted with a Fowler type trailing edge flap, the Full extended position will produce:", "options": [ { @@ -7070,8 +7070,8 @@ "explanation": "" }, "fovP15xE": { - "id": "fovP15xE", "type": "simple", + "id": "fovP15xE", "question": "On a wing fitted with a fowler type trailing edge flap, the Full extended position will produce:", "options": [ { @@ -7107,12 +7107,12 @@ }, { "id": "Q3YNJKH089", - "explanation": "", "learningObjectives": ["081.01.01.01.04"], + "explanation": "", "variants": { "kXhL4cRk": { - "id": "kXhL4cRk", "type": "simple", + "id": "kXhL4cRk", "question": "The density of the air at 40,000ft is approximately:\n ", "options": [ { @@ -7148,12 +7148,12 @@ }, { "id": "QWEUP3IAEL", - "explanation": "", "learningObjectives": ["081.01.02.01.01"], + "explanation": "", "variants": { "308T6Cfy": { - "id": "308T6Cfy", "type": "simple", + "id": "308T6Cfy", "question": "Assuming incompressible flow, when considering streamlines in the vicinity of an aerofoil, which of the following answers is correct?", "options": [ { @@ -7189,12 +7189,12 @@ }, { "id": "Q40E7PB62Z", - "explanation": "", "learningObjectives": ["081.01.01.01.11"], + "explanation": "", "variants": { "M2qe8zQ2": { - "id": "M2qe8zQ2", "type": "simple", + "id": "M2qe8zQ2", "question": "Bernoulli’s equation can be written as: (pt = total pressure, ps = static pressure, q = dynamic pressure)", "options": [ { @@ -7236,12 +7236,12 @@ }, { "id": "Q4130RHCKY", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "x1K9LQAn": { - "id": "x1K9LQAn", "type": "simple", + "id": "x1K9LQAn", "question": "An aeroplane’s Lift/Drag (L/D) ratio is...", "options": [ { @@ -7277,12 +7277,12 @@ }, { "id": "Q419YUGCYT", - "explanation": "", "learningObjectives": ["081.01.01.05.12"], + "explanation": "", "variants": { "klwsmLxO": { - "id": "klwsmLxO", "type": "simple", + "id": "klwsmLxO", "question": "The angle of attack of a two-dimensional wing section is the angle between", "options": [ { @@ -7323,12 +7323,12 @@ }, { "id": "Q41SYBFWSV", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "paK9wkwM": { - "id": "paK9wkwM", "type": "simple", + "id": "paK9wkwM", "question": "Considering a positive cambered aerofoil, the pitch moment when Cl=0 is:", "options": [ { @@ -7364,12 +7364,12 @@ }, { "id": "Q42IK0WI9T", - "explanation": "", "learningObjectives": ["081.01.01.01.11"], + "explanation": "", "variants": { "qlfHuAbM": { - "id": "qlfHuAbM", "type": "simple", + "id": "qlfHuAbM", "question": "Bernoulli's theorem states the following:", "options": [ { @@ -7405,12 +7405,12 @@ }, { "id": "Q44482J6DP", - "explanation": "", "learningObjectives": ["081.01.05.03.01"], + "explanation": "", "variants": { "atNFgoyQ": { - "id": "atNFgoyQ", "type": "simple", + "id": "atNFgoyQ", "question": "An increase in Parasite Drag will:", "options": [ { @@ -7446,12 +7446,12 @@ }, { "id": "Q45034WW53", - "explanation": "", "learningObjectives": ["081.01", "081.03"], + "explanation": "", "variants": { "pT1odnab": { - "id": "pT1odnab", "type": "simple", + "id": "pT1odnab", "question": "Wing loading is the ratio between:", "options": [ { @@ -7487,12 +7487,12 @@ }, { "id": "Q4724J0PDN", - "explanation": "", "learningObjectives": ["081.01.09.01.09"], + "explanation": "", "variants": { "MaNqzr0u": { - "id": "MaNqzr0u", "type": "simple", + "id": "MaNqzr0u", "question": "During straight and level flight, the pilot starts extending flaps to the landing configuration. Due to a malfunction, the trailing edge flaps on the right wing remain retracted. If the malfunction goes unnoticed, the possible consequence is:", "options": [ { @@ -7528,12 +7528,12 @@ }, { "id": "QZ44QK92PV", - "explanation": "", "learningObjectives": ["081.01", "081.05"], + "explanation": "", "variants": { "pDRWrtY8": { - "id": "pDRWrtY8", "type": "simple", + "id": "pDRWrtY8", "question": "Spoilers mounted on the wing upper surface can be used to:", "options": [ { @@ -7574,12 +7574,12 @@ }, { "id": "QTRZ5U5URM", - "explanation": "", "learningObjectives": ["081.01.04.03.05"], + "explanation": "", "variants": { "76DC0Sb8": { - "id": "76DC0Sb8", "type": "simple", + "id": "76DC0Sb8", "question": "Which of the following are means to reduce induced drag?", "options": [ { @@ -7620,12 +7620,12 @@ }, { "id": "Q4BZGG65LP", - "explanation": "", "learningObjectives": ["081.01.05.02.01"], + "explanation": "", "variants": { "v3ExHhvx": { - "id": "v3ExHhvx", "type": "simple", + "id": "v3ExHhvx", "question": "Which drag components make up parasite drag?\n\n- Pressure drag\n\n- Friction drag\n\n- Induced drag\n\n- Interference drag\n\nThe combination that regroups all of the correct statements is:", "options": [ { @@ -7661,12 +7661,12 @@ }, { "id": "Q4C5WV5JQD", - "explanation": "", "learningObjectives": ["081.01.03.03.01"], + "explanation": "", "variants": { "q6eLLsnH": { - "id": "q6eLLsnH", "type": "simple", + "id": "q6eLLsnH", "question": "The correct drag formula is:\n(note: RHO = density)", "options": [ { @@ -7702,12 +7702,12 @@ }, { "id": "Q4D04FXMQ4", - "explanation": "", "learningObjectives": ["081.01.01.01.13"], + "explanation": "", "variants": { "6Mh7BSwD": { - "id": "6Mh7BSwD", "type": "simple", + "id": "6Mh7BSwD", "question": "Which of the following statements, about a venturi in a subsonic airflow are correct? \n1. The dynamic pressures in the undisturbed flow and in the throat are equal. \n2. The total pressures in the undisturbed flow and in the throat are equal.", "options": [ { @@ -7743,12 +7743,12 @@ }, { "id": "Q4ESJGKGAV", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "Xb97tQXa": { - "id": "Xb97tQXa", "type": "simple", + "id": "Xb97tQXa", "question": "Assuming no flow separation and no compressibility effects the location of the centre of pressure of a positively cambered aerofoil section", "options": [ { @@ -7781,8 +7781,8 @@ "explanation": "" }, "MiwyMEK2": { - "id": "MiwyMEK2", "type": "simple", + "id": "MiwyMEK2", "question": "Assuming no flow separation and no compressibility effects the location of the centre of pressure of a symmetrical aerofoil section", "options": [ { @@ -7818,12 +7818,12 @@ }, { "id": "Q4FSMMIRB3", - "explanation": "", "learningObjectives": ["081.01.04.02.07"], + "explanation": "", "variants": { "h1fuR1uf": { - "id": "h1fuR1uf", "type": "simple", + "id": "h1fuR1uf", "question": "Upon extension of Fowler flaps whilst maintaining the same angle of attack:", "options": [ { @@ -7859,12 +7859,12 @@ }, { "id": "Q4GCUN20V9", - "explanation": "", "learningObjectives": ["081.01.01.01.09"], + "explanation": "", "variants": { "hgQp7o0l": { - "id": "hgQp7o0l", "type": "simple", + "id": "hgQp7o0l", "question": "The total pressure:\n(note: rho = density)", "options": [ { @@ -7900,12 +7900,12 @@ }, { "id": "Q4JA8JJDUK", - "explanation": "", "learningObjectives": ["081.01.03.02.01"], + "explanation": "", "variants": { "pl64lqdt": { - "id": "pl64lqdt", "type": "simple", + "id": "pl64lqdt", "question": "In the lift formula, Lift = CL x ½rhoV² x S, V is... and S is ..:.....", "options": [ { @@ -7941,12 +7941,12 @@ }, { "id": "Q4OFCZL7KO", - "explanation": "", "learningObjectives": ["081.01.01.05.05"], + "explanation": "", "variants": { "W9pNahym": { - "id": "W9pNahym", "type": "simple", + "id": "W9pNahym", "question": "The wing platform that gives a constant lift value along the whole area is...", "options": [ { @@ -7982,12 +7982,12 @@ }, { "id": "Q4OYBADOF8", - "explanation": "", "learningObjectives": ["081.01.09.02.06"], + "explanation": "", "variants": { "p08uuHvv": { - "id": "p08uuHvv", "type": "simple", + "id": "p08uuHvv", "question": "Which of the following combinations will result in a larger decrease in C~DI~?", "options": [ { @@ -8023,12 +8023,12 @@ }, { "id": "Q4TNUDMX3H", - "explanation": "", "learningObjectives": ["081.01.03.03.01"], + "explanation": "", "variants": { "T55t6yQS": { - "id": "T55t6yQS", "type": "simple", + "id": "T55t6yQS", "question": "Based on the two dimensional drag formula, drag is:", "options": [ { @@ -8064,12 +8064,12 @@ }, { "id": "Q4U4M4XNCK", - "explanation": "", "learningObjectives": ["081.01.06.01.02"], + "explanation": "", "variants": { "IXoSvYBN": { - "id": "IXoSvYBN", "type": "simple", + "id": "IXoSvYBN", "question": "Which statements, about an aeroplane leaving ground effect at constant angle of attack are correct or incorrect?\n1) The lift coefficient CL decreases.2) The induced drag coefficient CD~i~ increases.", "options": [ { @@ -8105,12 +8105,12 @@ }, { "id": "Q4X1FWM90C", - "explanation": "", "learningObjectives": ["081.01.03.02.01"], + "explanation": "", "variants": { "CXmykVba": { - "id": "CXmykVba", "type": "simple", + "id": "CXmykVba", "question": "What is coefficient of lift, C~L~?", "options": [ { @@ -8146,12 +8146,12 @@ }, { "id": "Q4YBSFSNT4", - "explanation": "", "learningObjectives": ["081.01.01.04.04"], + "explanation": "", "variants": { "UQGBPZLU": { - "id": "UQGBPZLU", "type": "simple", + "id": "UQGBPZLU", "question": "The relative thickness of an aerofoil is expressed in:", "options": [ { @@ -8192,12 +8192,12 @@ }, { "id": "Q51HYMU76P", - "explanation": "", "learningObjectives": ["081.01.03.03.02"], + "explanation": "", "variants": { "NNueWBpX": { - "id": "NNueWBpX", "type": "simple", + "id": "NNueWBpX", "question": "Refer to figure. \n Assuming all bodies have the same cross-sectional area and are in motion, which body will have the lowest pressure drag?", "options": [ { @@ -8233,12 +8233,12 @@ }, { "id": "Q532QBE7LM", - "explanation": "", "learningObjectives": ["081.01.01.05.08"], + "explanation": "", "variants": { "eNmokSDN": { - "id": "eNmokSDN", "type": "simple", + "id": "eNmokSDN", "question": "The aspect ratio of a wing is the ratio between the:", "options": [ { @@ -8279,12 +8279,12 @@ }, { "id": "Q54HTS9AJM", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "T4ZwHX97": { - "id": "T4ZwHX97", "type": "simple", + "id": "T4ZwHX97", "question": "When deploying speedbrakes, you can expect the minimum drag to (1) _____ and the minimum drag speed to (2)_____.", "options": [ { @@ -8320,12 +8320,12 @@ }, { "id": "Q551KT5OED", - "explanation": "", "learningObjectives": ["081.01.02.09.02"], + "explanation": "", "variants": { "cph2chvC": { - "id": "cph2chvC", "type": "simple", + "id": "cph2chvC", "question": "Consider a graph showing lift coefficient vs angle-of-attack (C~L~ vs α) for a symmetrical aerofoil. Which of the following is defined by the point which crosses the vertical axis of this graph?", "options": [ { @@ -8361,12 +8361,12 @@ }, { "id": "Q55ZVQVEV8", - "explanation": "", "learningObjectives": ["081.01.01.01.16"], + "explanation": "", "variants": { "EIqBJHqv": { - "id": "EIqBJHqv", "type": "simple", + "id": "EIqBJHqv", "question": "The equation of continuity states that:", "options": [ { @@ -8402,12 +8402,12 @@ }, { "id": "Q59TQ0LBIW", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "eYJRUd71": { - "id": "eYJRUd71", "type": "simple", + "id": "eYJRUd71", "question": "On the approach to land, ground effect could begin to be felt at:", "options": [ { @@ -8443,12 +8443,12 @@ }, { "id": "Q5BXR7ZU6M", - "explanation": "", "learningObjectives": ["081.01.01.04.06"], + "explanation": "", "variants": { "nDEIzvs2": { - "id": "nDEIzvs2", "type": "simple", + "id": "nDEIzvs2", "question": "In a symmetrical airfoil the mean camber line\nis:", "options": [ { @@ -8484,12 +8484,12 @@ }, { "id": "Q5EXJ9VXV0", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "1UKLhmdA": { - "id": "1UKLhmdA", "type": "simple", + "id": "1UKLhmdA", "question": "The drag of an aeroplane is 850 Newton. The wingspan is increase by 10 %. What is the new value of drag?", "options": [ { @@ -8525,12 +8525,12 @@ }, { "id": "QMK568ED9N", - "explanation": "", "learningObjectives": ["081.01.01.01.16"], + "explanation": "", "variants": { "oMu98wvU": { - "id": "oMu98wvU", "type": "simple", + "id": "oMu98wvU", "question": "For a subsonic flow the continuity equation states that if the cross-sectional area of a tube decreases, the speed of the flow:", "options": [ { @@ -8570,8 +8570,8 @@ "explanation": "" }, "lzzMnW4x": { - "id": "lzzMnW4x", "type": "simple", + "id": "lzzMnW4x", "question": "For a subsonic flow the continuity equation states that if the cross-sectional area of a tube increases, the speed of the flow:", "options": [ { @@ -8607,12 +8607,12 @@ }, { "id": "Q5GN8UE3CM", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "uil1FV5G": { - "id": "uil1FV5G", "type": "simple", + "id": "uil1FV5G", "question": "The relationship between induced drag and the aspect ratio is", "options": [ { @@ -8653,12 +8653,12 @@ }, { "id": "Q5IVH5PQL5", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "5DutrQh2": { - "id": "5DutrQh2", "type": "simple", + "id": "5DutrQh2", "question": "Regarding a symmetric aerofoil section, which statements are correct or incorrect?\n1) The angle of attack is zero when the lift coefficient equals zero.\n2) A nose up pitching moment exists when the lift coefficient equals zero.", "options": [ { @@ -8694,12 +8694,12 @@ }, { "id": "Q5JX5WK4W3", - "explanation": "", "learningObjectives": ["081.01.01.01.02"], + "explanation": "", "variants": { "cpFbYAVh": { - "id": "cpFbYAVh", "type": "simple", + "id": "cpFbYAVh", "question": "Which formula or equation describes the relationship between force (F), acceleration (and mass (m)?", "options": [ { @@ -8735,12 +8735,12 @@ }, { "id": "Q5LAS7ZG3G", - "explanation": "", "learningObjectives": ["081.01.09.01.05"], + "explanation": "", "variants": { "msLRaPbe": { - "id": "msLRaPbe", "type": "simple", + "id": "msLRaPbe", "question": "A plain flap will increase CL~MAX~ by:", "options": [ { @@ -8781,12 +8781,12 @@ }, { "id": "Q5M9UFS3NO", - "explanation": "", "learningObjectives": ["081.01.05.03.01"], + "explanation": "", "variants": { "4ghNVEyI": { - "id": "4ghNVEyI", "type": "simple", + "id": "4ghNVEyI", "question": "A body is placed in a certain airstream. If the airstream velocity increases by a factor of 4, the parasite drag will increase by a factor of", "options": [ { @@ -8822,12 +8822,12 @@ }, { "id": "Q5MCDQZ70R", - "explanation": "", "learningObjectives": ["081.01", "081.08"], + "explanation": "", "variants": { "e41UzCN3": { - "id": "e41UzCN3", "type": "simple", + "id": "e41UzCN3", "question": "Which of these conditions will have least effect on control in asymmetric flight?", "options": [ { @@ -8863,12 +8863,12 @@ }, { "id": "Q5ME78C7BF", - "explanation": "", "learningObjectives": ["081.01.01.03.08"], + "explanation": "", "variants": { "w9J1tgsQ": { - "id": "w9J1tgsQ", "type": "simple", + "id": "w9J1tgsQ", "question": "The term angle of attack in a two dimensional flow is defined as the angle:", "options": [ { @@ -8910,12 +8910,12 @@ }, { "id": "Q5MI4H94R7", - "explanation": "", "learningObjectives": ["081.01.01.01.01"], + "explanation": "", "variants": { "c2XnhkO1": { - "id": "c2XnhkO1", "type": "simple", + "id": "c2XnhkO1", "question": "State the correct SI unit which is used to express \"work\"?", "options": [ { @@ -8951,12 +8951,12 @@ }, { "id": "Q5NIYS7LNB", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "lE5EXko7": { - "id": "lE5EXko7", "type": "simple", + "id": "lE5EXko7", "question": "Assuming no flow separation, which of these statements about the flow around an aerofoil as the angle of attack decreases are correct or incorrect?\n\n1. The stagnation point moves up.\n\n2. The point of lowest static pressure moves forward.", "options": [ { @@ -9000,8 +9000,8 @@ "explanation": "" }, "jVC8xmKg": { - "id": "jVC8xmKg", "type": "simple", + "id": "jVC8xmKg", "question": "Assuming no flow separation, which of these statements about the flow around an aerofoil as the angle of attack increases are correct or incorrect?\n\n1. The stagnation point moves up.\n\n2. The point of lowest static pressure moves forward.", "options": [ { @@ -9034,8 +9034,8 @@ "explanation": "" }, "oVc3bbGc": { - "id": "oVc3bbGc", "type": "simple", + "id": "oVc3bbGc", "question": "Assuming no flow separation, which of these statements about the flow around an aerofoil as the angle of attack decreases are correct or incorrect?\n\n1. The stagnation point moves up.\n\n2. The point of lowest static pressure moves aft.", "options": [ { @@ -9071,12 +9071,12 @@ }, { "id": "Q5NMWMJMI4", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "eGCaa3A0": { - "id": "eGCaa3A0", "type": "simple", + "id": "eGCaa3A0", "question": "Following the deployment of leading edge devices, while the trailing edge flaps remain retracted:", "options": [ { @@ -9112,12 +9112,12 @@ }, { "id": "Q5OE74M3X4", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "sq7YwxL5": { - "id": "sq7YwxL5", "type": "simple", + "id": "sq7YwxL5", "question": "In straight and level flight at a speed of 1.1 VS, the lift coefficient, expressed as a percentage of its maximum CLMAX, would be", "options": [ { @@ -9150,8 +9150,8 @@ "explanation": "" }, "VTAeQiQh": { - "id": "VTAeQiQh", "type": "simple", + "id": "VTAeQiQh", "question": "In straight and level flight at a speed of 1.2 VS, the lift coefficient, expressed as a percentage of its maximum CLMAX, would be", "options": [ { @@ -9184,8 +9184,8 @@ "explanation": "" }, "DwV9nL2h": { - "id": "DwV9nL2h", "type": "simple", + "id": "DwV9nL2h", "question": "In straight and level flight at a speed of 1.3 VS, the lift coefficient, expressed as a percentage of its maximum CLMAX, would be", "options": [ { @@ -9218,8 +9218,8 @@ "explanation": "" }, "BI8ZG6g8": { - "id": "BI8ZG6g8", "type": "simple", + "id": "BI8ZG6g8", "question": "In straight and level flight at a speed of 1.4 VS, the lift coefficient, expressed as a percentage of its maximum CLMAX, would be", "options": [ { @@ -9252,8 +9252,8 @@ "explanation": "" }, "fNPikBHA": { - "id": "fNPikBHA", "type": "simple", + "id": "fNPikBHA", "question": "In straight and level flight at a speed of 1.6 VS, the lift coefficient, expressed as a percentage of its maximum CLMAX, would be", "options": [ { @@ -9286,8 +9286,8 @@ "explanation": "" }, "hnNa27iE": { - "id": "hnNa27iE", "type": "simple", + "id": "hnNa27iE", "question": "In straight and level flight at a speed of 1.8 VS, the lift coefficient, expressed as a percentage of its maximum CLMAX, would be", "options": [ { @@ -9320,8 +9320,8 @@ "explanation": "" }, "9b3prZOA": { - "id": "9b3prZOA", "type": "simple", + "id": "9b3prZOA", "question": "In straight and level flight at a speed of 1.7 VS, the lift coefficient, expressed as a percentage of its maximum CLMAX, would be", "options": [ { @@ -9354,8 +9354,8 @@ "explanation": "" }, "56wZFBNM": { - "id": "56wZFBNM", "type": "simple", + "id": "56wZFBNM", "question": "In straight and level flight at a speed of 1.5 VS, the lift coefficient, expressed as a percentage of its maximum CLMAX, would be", "options": [ { @@ -9391,12 +9391,12 @@ }, { "id": "QBPBANP9EK", - "explanation": "", "learningObjectives": ["081.01.01.05.08"], + "explanation": "", "variants": { "ryxR44Nn": { - "id": "ryxR44Nn", "type": "simple", + "id": "ryxR44Nn", "question": "High aspect ratio, as compared with low aspect ratio, has the effect of:", "options": [ { @@ -9437,12 +9437,12 @@ }, { "id": "Q5QZLPP0LV", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "HizmLZ6I": { - "id": "HizmLZ6I", "type": "simple", + "id": "HizmLZ6I", "question": "Regarding a positively cambered aerofoil section, which statement is correct? \n1.The angle of attack has a negative value when the lift coefficient equals zero\n2. A nose down pitching moment exists when the lift coefficient equals zero.", "options": [ { @@ -9478,12 +9478,12 @@ }, { "id": "Q5V16OMDON", - "explanation": "", "learningObjectives": ["081.01.06.01.01"], + "explanation": "", "variants": { "jEuAILyn": { - "id": "jEuAILyn", "type": "simple", + "id": "jEuAILyn", "question": "On an aircraft leaving ground effect after lift-off, wing tip vortices (1) _____ and the induced angle of attack will (2) _____.", "options": [ { @@ -9519,12 +9519,12 @@ }, { "id": "Q5VRA9IB9Z", - "explanation": "", "learningObjectives": ["081.01.05.05.01"], + "explanation": "", "variants": { "GrhsKZT4": { - "id": "GrhsKZT4", "type": "simple", + "id": "GrhsKZT4", "question": "The total drag of a three dimensional wing consists of", "options": [ { @@ -9565,12 +9565,12 @@ }, { "id": "Q5WYQ7C3OT", - "explanation": "", "learningObjectives": ["081.01.09.03.01"], + "explanation": "", "variants": { "Nz0KdsNa": { - "id": "Nz0KdsNa", "type": "simple", + "id": "Nz0KdsNa", "question": "Vortex generators re-energise the boundary layer and", "options": [ { @@ -9606,12 +9606,12 @@ }, { "id": "Q608FU41L4", - "explanation": "", "learningObjectives": ["081.01.05.01.01"], + "explanation": "", "variants": { "QA9jm4hq": { - "id": "QA9jm4hq", "type": "simple", + "id": "QA9jm4hq", "question": "Total drag is the sum of", "options": [ { @@ -9652,12 +9652,12 @@ }, { "id": "Q60W70OCDI", - "explanation": "", "learningObjectives": ["081.01.12.01.02"], + "explanation": "", "variants": { "wQYJ3VRo": { - "id": "wQYJ3VRo", "type": "simple", + "id": "wQYJ3VRo", "question": "How are stalling speed, stalling angle of attack and control changed by aircraft icing?", "options": [ { @@ -9693,12 +9693,12 @@ }, { "id": "Q613D2JVNL", - "explanation": "", "learningObjectives": ["081.01.04.03.03"], + "explanation": "", "variants": { "Qt741gXL": { - "id": "Qt741gXL", "type": "simple", + "id": "Qt741gXL", "question": "If you are flying at the rear of the drag curve and your CAS decreases, what happens to the parasite, induced and total drag?", "options": [ { @@ -9734,12 +9734,12 @@ }, { "id": "QH6PWZOVO2", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "ZA3EhwYT": { - "id": "ZA3EhwYT", "type": "simple", + "id": "ZA3EhwYT", "question": "A symmetric aerofoil will generate:", "options": [ { @@ -9775,12 +9775,12 @@ }, { "id": "Q63E4BAAFS", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "L65Wvy8V": { - "id": "L65Wvy8V", "type": "simple", + "id": "L65Wvy8V", "question": "An object has a drag of 785 N at sea level, assuming ISA conditions and that the object is travelling at the same speed, the drag of the object at 6 000 ft is roughly:", "options": [ { @@ -9816,12 +9816,12 @@ }, { "id": "Q650BSRDEG", - "explanation": "", "learningObjectives": ["081.01.01.01.16"], + "explanation": "", "variants": { "ch933Ylb": { - "id": "ch933Ylb", "type": "simple", + "id": "ch933Ylb", "question": "Consider a steady flow through a stream tube at a given constant velocity. An increase in the flow's temperature will:", "options": [ { @@ -9854,8 +9854,8 @@ "explanation": "" }, "3ME6oSBl": { - "id": "3ME6oSBl", "type": "simple", + "id": "3ME6oSBl", "question": "Consider a steady flow through a stream tube at a given constant velocity. An increase in the flow's temperature will:", "options": [ { @@ -9891,12 +9891,12 @@ }, { "id": "Q6542TKS71", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "C00w6qNF": { - "id": "C00w6qNF", "type": "simple", + "id": "C00w6qNF", "question": "An aeroplane accelerates from 80 kt to 160 kt at a load factor equal to 1. By what factors will the induced drag coefficient and the induced drag change?", "options": [ { @@ -9932,12 +9932,12 @@ }, { "id": "Q65XRC7BT8", - "explanation": "", "learningObjectives": ["081.01.12.01.01"], + "explanation": "", "variants": { "4YzLQJcd": { - "id": "4YzLQJcd", "type": "simple", + "id": "4YzLQJcd", "question": "What locations are the most susceptible to ice build-up during flight?", "options": [ { @@ -9973,12 +9973,12 @@ }, { "id": "Q66E1UMHJJ", - "explanation": "", "learningObjectives": ["081.01.03.03.01"], + "explanation": "", "variants": { "bfOfI5DI": { - "id": "bfOfI5DI", "type": "simple", + "id": "bfOfI5DI", "question": "The correct drag formula can be written as...(rho = density)", "options": [ { @@ -10014,12 +10014,12 @@ }, { "id": "Q67RQ5TW9G", - "explanation": "", "learningObjectives": ["081.01.02.03.01"], + "explanation": "", "variants": { "SruLPo21": { - "id": "SruLPo21", "type": "simple", + "id": "SruLPo21", "question": "Assuming no flow separation, when speed is decreased in straight and level flight on a positively cambered aerofoil, what happens to the 1 centre of pressure and 2 the magnitude of the total lift force?", "options": [ { @@ -10055,12 +10055,12 @@ }, { "id": "QCN3HW8LYK", - "explanation": "", "learningObjectives": ["081.01.09.01.07"], + "explanation": "", "variants": { "AUNgRurC": { - "id": "AUNgRurC", "type": "simple", + "id": "AUNgRurC", "question": "What is the most effective flap system?", "options": [ { @@ -10101,12 +10101,12 @@ }, { "id": "Q6BGVLHLM4", - "explanation": "", "learningObjectives": ["081.01.01.05.07"], + "explanation": "", "variants": { "NDAqk8Wr": { - "id": "NDAqk8Wr", "type": "simple", + "id": "NDAqk8Wr", "question": "The Mean Aerodynamic Chord (MAC) for a given wing of any platform is basically:", "options": [ { @@ -10148,12 +10148,12 @@ }, { "id": "Q6C6X9EWM5", - "explanation": "", "learningObjectives": ["081.01.09.02.07"], + "explanation": "", "variants": { "brwMrtPc": { - "id": "brwMrtPc", "type": "simple", + "id": "brwMrtPc", "question": "Slats are:", "options": [ { @@ -10189,12 +10189,12 @@ }, { "id": "Q6CHL0S37G", - "explanation": "", "learningObjectives": ["081.01.09.01.08"], + "explanation": "", "variants": { "WdynWhja": { - "id": "WdynWhja", "type": "simple", + "id": "WdynWhja", "question": "A crew calculate speeds for a take-off using 15⁰ of flap but, due to distraction, perform the take off with flaps fully retracted. Which statement is true?", "options": [ { @@ -10230,12 +10230,12 @@ }, { "id": "Q6CQTZAAUH", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "UT9dAN60": { - "id": "UT9dAN60", "type": "simple", + "id": "UT9dAN60", "question": "What is the effect of increasing wing aspect ratio on induced drag?", "options": [ { @@ -10268,8 +10268,8 @@ "explanation": "" }, "uXXrfXVp": { - "id": "uXXrfXVp", "type": "simple", + "id": "uXXrfXVp", "question": "What is the effect of increasing wing aspect ratio on induced drag?", "options": [ { @@ -10305,12 +10305,12 @@ }, { "id": "Q6F0RD2U8Q", - "explanation": "", "learningObjectives": ["081.01", "081.03"], + "explanation": "", "variants": { "R22Ivjg4": { - "id": "R22Ivjg4", "type": "simple", + "id": "R22Ivjg4", "question": "The most important problem of ice accretion on a transport aeroplane during flight is:", "options": [ { @@ -10348,8 +10348,8 @@ "explanation": "" }, "j9E12iYc": { - "id": "j9E12iYc", "type": "simple", + "id": "j9E12iYc", "question": "The most important problem of ice accretion on a transport aeroplane during flight is:", "options": [ { @@ -10382,8 +10382,8 @@ "explanation": "" }, "3mlrU8Z8": { - "id": "3mlrU8Z8", "type": "simple", + "id": "3mlrU8Z8", "question": "The most important problem of ice accretion on a transport aeroplane during flight is:", "options": [ { @@ -10419,12 +10419,12 @@ }, { "id": "Q6FL3821DH", - "explanation": "", "learningObjectives": ["081.01.06.01.02"], + "explanation": "", "variants": { "cy6ONurz": { - "id": "cy6ONurz", "type": "simple", + "id": "cy6ONurz", "question": "Which statement, about an aeroplane entering ground effect at constant angle of attack, is correct?\n\n1. The lift coefficient CL increases.\n\n2. The induced drag coefficient CD~i~ increases.", "options": [ { @@ -10460,12 +10460,12 @@ }, { "id": "QNVFYAT8WZ", - "explanation": "", "learningObjectives": ["081.01.01.01.07"], + "explanation": "", "variants": { "XSB0lGkO": { - "id": "XSB0lGkO", "type": "simple", + "id": "XSB0lGkO", "question": "The (subsonic) static pressure:", "options": [ { @@ -10503,8 +10503,8 @@ "explanation": "" }, "VHjTgnC2": { - "id": "VHjTgnC2", "type": "simple", + "id": "VHjTgnC2", "question": "The (subsonic) static pressure:", "options": [ { @@ -10540,12 +10540,12 @@ }, { "id": "Q6HI0PTRU1", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "Zb9EcXk4": { - "id": "Zb9EcXk4", "type": "simple", + "id": "Zb9EcXk4", "question": "Subsonic flow over a cambered airfoil at 4deg angle of\nattack will cause ....(1).... on upper surface and ....(2).... over\nlower surface:", "options": [ { @@ -10581,12 +10581,12 @@ }, { "id": "Q6MGUAO5LX", - "explanation": "", "learningObjectives": ["081.01.09.02.02"], + "explanation": "", "variants": { "JlWcObF8": { - "id": "JlWcObF8", "type": "simple", + "id": "JlWcObF8", "question": "The function of the slot between an extended slat and the leading edge of the wing is to", "options": [ { @@ -10622,12 +10622,12 @@ }, { "id": "Q6OBJPOEY2", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "LIPN1M0k": { - "id": "LIPN1M0k", "type": "simple", + "id": "LIPN1M0k", "question": "An aircraft is in level flight at a speed of 1.6Vs. The value of CL is 0.35\nWhat will be the value of CL if speed is reduced to 1.1 Vs?", "options": [ { @@ -10663,12 +10663,12 @@ }, { "id": "Q6R4MS3CYN", - "explanation": "", "learningObjectives": ["081.01.09.01.08"], + "explanation": "", "variants": { "S9Z0TXvN": { - "id": "S9Z0TXvN", "type": "simple", + "id": "S9Z0TXvN", "question": "A medium sized jet is on final approach, the pilots configure for a full flaps landing. The left wing leading-edge slats do not extend. Which statement is true?", "options": [ { @@ -10704,12 +10704,12 @@ }, { "id": "Q6SG3SNISV", - "explanation": "", "learningObjectives": ["081.01.04.03.15"], + "explanation": "", "variants": { "b9ynJzAD": { - "id": "b9ynJzAD", "type": "simple", + "id": "b9ynJzAD", "question": "Typically the C~L~/C~D~ ratio is:", "options": [ { @@ -10745,12 +10745,12 @@ }, { "id": "Q6T2HDAKGH", - "explanation": "", "learningObjectives": ["081.01.01.04.02"], + "explanation": "", "variants": { "kr1YskTv": { - "id": "kr1YskTv", "type": "simple", + "id": "kr1YskTv", "question": "A line connecting the leading and trailing edge midway between the upper and lower surface of an aerofoil, is the definition of the..", "options": [ { @@ -10791,12 +10791,12 @@ }, { "id": "Q704LAX6MK", - "explanation": "", "learningObjectives": ["081.01.04.03.04"], + "explanation": "", "variants": { "fBWOYPRb": { - "id": "fBWOYPRb", "type": "simple", + "id": "fBWOYPRb", "question": "For a given aircraft at a given height (and therefore constant air density), doubling the IAS will increase the Parasite Drag:", "options": [ { @@ -10832,12 +10832,12 @@ }, { "id": "Q712GXEP9A", - "explanation": "", "learningObjectives": ["081.01.02.01.01"], + "explanation": "", "variants": { "pyv6BOpI": { - "id": "pyv6BOpI", "type": "simple", + "id": "pyv6BOpI", "question": "Which statement concerning the local flow pattern around a wing is correct?", "options": [ { @@ -10878,12 +10878,12 @@ }, { "id": "Q71VJ4OIV4", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "xFObcb05": { - "id": "xFObcb05", "type": "simple", + "id": "xFObcb05", "question": "Assuming no flow separation, which of these statements about the flow around an aerofoil as the angle of attack decreases are correct or incorrect? \n\ni The stagnation point moves down\n II The point of lowest static pressure moves aft.", "options": [ { @@ -10919,12 +10919,12 @@ }, { "id": "Q726B3RYSE", - "explanation": "", "learningObjectives": ["081.01.01.04.03"], + "explanation": "", "variants": { "dpQvZJ6V": { - "id": "dpQvZJ6V", "type": "simple", + "id": "dpQvZJ6V", "question": "The airfoil chord line is:", "options": [ { @@ -10957,8 +10957,8 @@ "explanation": "" }, "lS4ewRRs": { - "id": "lS4ewRRs", "type": "simple", + "id": "lS4ewRRs", "question": "The airfoil chord line is:", "options": [ { @@ -10994,12 +10994,12 @@ }, { "id": "QA86TVM5PG", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "zZbfTTaZ": { - "id": "zZbfTTaZ", "type": "simple", + "id": "zZbfTTaZ", "question": "Induced drag is the result of:", "options": [ { @@ -11040,12 +11040,12 @@ }, { "id": "Q73F9M2DIG", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "KpiD85sP": { - "id": "KpiD85sP", "type": "simple", + "id": "KpiD85sP", "question": "Refer to the image. \nThe high lift device shown in the figure is a:", "options": [ { @@ -11081,12 +11081,12 @@ }, { "id": "Q7411LR582", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "FeMqZbKN": { - "id": "FeMqZbKN", "type": "simple", + "id": "FeMqZbKN", "question": "The use of flaps allows an aircraft to produce (1) _____ lift at a (2) _____ speed, and with (3) _____ drag.", "options": [ { @@ -11122,12 +11122,12 @@ }, { "id": "Q75Z397HQY", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "ZoznCjHv": { - "id": "ZoznCjHv", "type": "simple", + "id": "ZoznCjHv", "question": "(For this question use the image in the annex). The high lift device shown in the figure is a:", "options": [ { @@ -11163,12 +11163,12 @@ }, { "id": "Q76VS5IZY6", - "explanation": "", "learningObjectives": ["081.01", "081.05"], + "explanation": "", "variants": { "WYYFuaSf": { - "id": "WYYFuaSf", "type": "simple", + "id": "WYYFuaSf", "question": "When the control column is moved forward and to the right:", "options": [ { @@ -11201,8 +11201,8 @@ "explanation": "" }, "HOfOfsTq": { - "id": "HOfOfsTq", "type": "simple", + "id": "HOfOfsTq", "question": "When the control column is moved forward and to the right:", "options": [ { @@ -11238,12 +11238,12 @@ }, { "id": "Q7775DY326", - "explanation": "", "learningObjectives": ["081.01", "081.07"], + "explanation": "", "variants": { "dla3CbUO": { - "id": "dla3CbUO", "type": "simple", + "id": "dla3CbUO", "question": "Which aircraft configuration is most effected by ground effect.?", "options": [ { @@ -11279,12 +11279,12 @@ }, { "id": "Q77CGZ9H6L", - "explanation": "", "learningObjectives": ["081.01.09.01.08"], + "explanation": "", "variants": { "SMjyQGt6": { - "id": "SMjyQGt6", "type": "simple", + "id": "SMjyQGt6", "question": "During an approach and coming to land, the pilots configure for full flaps landing. However, the left leading edge slats do not extend. Which statement is true?", "options": [ { @@ -11320,12 +11320,12 @@ }, { "id": "Q79F9QBXSY", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "9Hnex2FW": { - "id": "9Hnex2FW", "type": "simple", + "id": "9Hnex2FW", "question": "Which of the following statements are true regarding the reduction in induced drag? ", "options": [ { @@ -11361,12 +11361,12 @@ }, { "id": "QTRER7DVBQ", - "explanation": "", "learningObjectives": ["081.01.09.01.06"], + "explanation": "", "variants": { "3eMpjeVI": { - "id": "3eMpjeVI", "type": "simple", + "id": "3eMpjeVI", "question": "Trailing edge flap extension will:", "options": [ { @@ -11404,8 +11404,8 @@ "explanation": "" }, "2FFrhfQ5": { - "id": "2FFrhfQ5", "type": "simple", + "id": "2FFrhfQ5", "question": "Trailing edge flap extension will:", "options": [ { @@ -11441,12 +11441,12 @@ }, { "id": "Q7EOIJK2PW", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "d49xyxDg": { - "id": "d49xyxDg", "type": "simple", + "id": "d49xyxDg", "question": "At stalling speed, the stall warning vane on the leading edge of small aeroplanes moves", "options": [ { @@ -11482,12 +11482,12 @@ }, { "id": "Q7FSML1MAM", - "explanation": "", "learningObjectives": ["081.01.01.05.09"], + "explanation": "", "variants": { "MbwHTHEP": { - "id": "MbwHTHEP", "type": "simple", + "id": "MbwHTHEP", "question": "Dihedral of the wing is:", "options": [ { @@ -11523,12 +11523,12 @@ }, { "id": "Q7HGREDFI6", - "explanation": "", "learningObjectives": ["081.01.01.05.04"], + "explanation": "", "variants": { "CiD5cEmy": { - "id": "CiD5cEmy", "type": "simple", + "id": "CiD5cEmy", "question": "If the wing area is increased, lift will:", "options": [ { @@ -11569,12 +11569,12 @@ }, { "id": "Q7HPKN74QW", - "explanation": "", "learningObjectives": ["081.01.01.04.02"], + "explanation": "", "variants": { "DpKDGGtY": { - "id": "DpKDGGtY", "type": "simple", + "id": "DpKDGGtY", "question": "Refer to figure. \n Name the leading and trailling edge devices in the attached figure.", "options": [ { @@ -11610,12 +11610,12 @@ }, { "id": "Q7I1W3VVGW", - "explanation": "", "learningObjectives": ["081.01.04.03.15"], + "explanation": "", "variants": { "yx21BbSI": { - "id": "yx21BbSI", "type": "simple", + "id": "yx21BbSI", "question": "Typically the CL/CD ratio is", "options": [ { @@ -11651,12 +11651,12 @@ }, { "id": "Q7I2O1EYY5", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "aaC3H9Vc": { - "id": "aaC3H9Vc", "type": "simple", + "id": "aaC3H9Vc", "question": "Which configuration will give the best Lift / Drag ratio?", "options": [ { @@ -11692,12 +11692,12 @@ }, { "id": "Q7J62LUDA0", - "explanation": "", "learningObjectives": ["081.01.01.01.09"], + "explanation": "", "variants": { "aba6YCXZ": { - "id": "aba6YCXZ", "type": "simple", + "id": "aba6YCXZ", "question": "The units of wing loading (W/S) ___ and dynamic pressure (q) ___ are?", "options": [ { @@ -11733,12 +11733,12 @@ }, { "id": "Q7KOW5IZI7", - "explanation": "", "learningObjectives": ["081.01.03.02.01"], + "explanation": "", "variants": { "cWhSIzrT": { - "id": "cWhSIzrT", "type": "simple", + "id": "cWhSIzrT", "question": "Lift is a function of:", "options": [ { @@ -11774,12 +11774,12 @@ }, { "id": "Q7L2Y5H5HA", - "explanation": "", "learningObjectives": ["081.01.05.02.01"], + "explanation": "", "variants": { "jo4xOSZN": { - "id": "jo4xOSZN", "type": "simple", + "id": "jo4xOSZN", "question": "In low subsonic flight Parasite Drag is made up of\nelements of:", "options": [ { @@ -11815,12 +11815,12 @@ }, { "id": "Q7MNHJX7MF", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "3K9pTOY6": { - "id": "3K9pTOY6", "type": "simple", + "id": "3K9pTOY6", "question": "The induced drag - if speed remains constant - is:", "options": [ { @@ -11856,12 +11856,12 @@ }, { "id": "Q7NI3EDYI6", - "explanation": "", "learningObjectives": ["081.01.06.04.02"], + "explanation": "", "variants": { "2VvQAswd": { - "id": "2VvQAswd", "type": "simple", + "id": "2VvQAswd", "question": "During landing of a low-winged jet aeroplane, the greatest elevator up deflection is normally required when the flaps are:", "options": [ { @@ -11897,12 +11897,12 @@ }, { "id": "Q7P2MY28JF", - "explanation": "", "learningObjectives": ["081.01.12.02.01"], + "explanation": "", "variants": { "vHsUcZKr": { - "id": "vHsUcZKr", "type": "simple", + "id": "vHsUcZKr", "question": "Some aeroplanes have a local reduction in fuselage cross-section (waistline or ?coke bottle' shape) \nThis is to?", "options": [ { @@ -11938,12 +11938,12 @@ }, { "id": "Q7QP8GGR97", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "dOZgd3HD": { - "id": "dOZgd3HD", "type": "simple", + "id": "dOZgd3HD", "question": "The induced drag:", "options": [ { @@ -11979,12 +11979,12 @@ }, { "id": "Q7RTD00LJ5", - "explanation": "", "learningObjectives": ["081.01.01.05.05"], + "explanation": "", "variants": { "dbEvljn4": { - "id": "dbEvljn4", "type": "simple", + "id": "dbEvljn4", "question": "Winglets", "options": [ { @@ -12020,12 +12020,12 @@ }, { "id": "Q7SF5GCRNU", - "explanation": "", "learningObjectives": ["081.01.09.02.08"], + "explanation": "", "variants": { "iFEQBkh7": { - "id": "iFEQBkh7", "type": "simple", + "id": "iFEQBkh7", "question": "All high lift devices allow us to fly safely at lower speeds by", "options": [ { @@ -12061,12 +12061,12 @@ }, { "id": "Q7SPLDPKUX", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "N5LPYqQn": { - "id": "N5LPYqQn", "type": "simple", + "id": "N5LPYqQn", "question": "What does the variable coefficient of lift depend on?", "options": [ { @@ -12102,12 +12102,12 @@ }, { "id": "Q7XD3GD81F", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "5EFZzsv1": { - "id": "5EFZzsv1", "type": "simple", + "id": "5EFZzsv1", "question": "On an aircraft with leading edge slats and trailing edge flaps, the slats on the left wing fail to extend during takeoff. What may occur?", "options": [ { @@ -12143,12 +12143,12 @@ }, { "id": "Q7XKBZKZ4X", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "GG8kCeZL": { - "id": "GG8kCeZL", "type": "simple", + "id": "GG8kCeZL", "question": "An aeroplane leaving the ground effect after take-off will experience..", "options": [ { @@ -12184,12 +12184,12 @@ }, { "id": "Q7ZH8MPWIZ", - "explanation": "", "learningObjectives": ["081.01.09.01.06"], + "explanation": "", "variants": { "VZ5hD9OD": { - "id": "VZ5hD9OD", "type": "simple", + "id": "VZ5hD9OD", "question": "An aircraft maintaining straight and level with no flaps deployed, has an airfoil with C~L~ = 0.38. If the pilot extends the flaps, what will happen to the C~L~?\nThe new C~L~ will be...", "options": [ { @@ -12225,12 +12225,12 @@ }, { "id": "Q804OS5MGK", - "explanation": "", "learningObjectives": ["081.01.04.02.05"], + "explanation": "", "variants": { "4duXlU88": { - "id": "4duXlU88", "type": "simple", + "id": "4duXlU88", "question": "In straight and level flight, the spanwise flow on an unswept wing is from the..", "options": [ { @@ -12266,12 +12266,12 @@ }, { "id": "QZ8Q0S38NF", - "explanation": "", "learningObjectives": ["081.01.12.02.01"], + "explanation": "", "variants": { "2mLqTKbD": { - "id": "2mLqTKbD", "type": "simple", + "id": "2mLqTKbD", "question": "On which type of drag does airframe ageing have the greatest influence?", "options": [ { @@ -12307,12 +12307,12 @@ }, { "id": "Q835YV62VA", - "explanation": "", "learningObjectives": ["081.01.05.07.02"], + "explanation": "", "variants": { "PcFxBCjN": { - "id": "PcFxBCjN", "type": "simple", + "id": "PcFxBCjN", "question": "Increasing dynamic pressure will have the following effect on the total drag of an aeroplane (all other factors of importance remaining constant):", "options": [ { @@ -12353,12 +12353,12 @@ }, { "id": "Q83XFPI6KH", - "explanation": "", "learningObjectives": ["081.01.03.03.02"], + "explanation": "", "variants": { "vnZ8Z4LA": { - "id": "vnZ8Z4LA", "type": "simple", + "id": "vnZ8Z4LA", "question": "Refer to figure 081-10.\nAssuming all bodies have the same cross-sectional area and are in motion, place these bodies in order of decreasing pressure drag. The correct answer is:", "options": [ { @@ -12394,8 +12394,8 @@ "explanation": "" }, "MznEYCGP": { - "id": "MznEYCGP", "type": "simple", + "id": "MznEYCGP", "question": "Refer to figure 081-10.\nAssuming all bodies have the same cross-sectional area and are in motion, place these bodies in order of increasing pressure drag. The correct answer is:", "options": [ { @@ -12431,12 +12431,12 @@ }, { "id": "Q85RHOWRB5", - "explanation": "", "learningObjectives": ["081.01.09.01.02"], + "explanation": "", "variants": { "kH3m2f09": { - "id": "kH3m2f09", "type": "simple", + "id": "kH3m2f09", "question": "Some wings are designed with a smaller angle of incidence towards the wing tip or a profile with a different camber towards the wing tip. The reason for this is to...", "options": [ { @@ -12472,12 +12472,12 @@ }, { "id": "Q889G5EIDA", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "0ydyZG5K": { - "id": "0ydyZG5K", "type": "simple", + "id": "0ydyZG5K", "question": "The point in the image giving the lowest speed in unaccelerated horizontal flight is", "options": [ { @@ -12510,8 +12510,8 @@ "explanation": "" }, "ry6QRgl7": { - "id": "ry6QRgl7", "type": "simple", + "id": "ry6QRgl7", "question": "The point in the image giving the lowest speed in unaccelerated flight is", "options": [ { @@ -12547,12 +12547,12 @@ }, { "id": "QXHCRKA8W8", - "explanation": "", "learningObjectives": ["081.01.01.05.10"], + "explanation": "", "variants": { "VKzPnA2l": { - "id": "VKzPnA2l", "type": "simple", + "id": "VKzPnA2l", "question": "Considering a rectangular unswept wing, which statement is correct?", "options": [ { @@ -12593,12 +12593,12 @@ }, { "id": "Q8AAZTE6J4", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "vM2IqpK9": { - "id": "vM2IqpK9", "type": "simple", + "id": "vM2IqpK9", "question": "Extending flap will (1)___ CL, (2)___ speed and (3)___ stall speed?", "options": [ { @@ -12634,12 +12634,12 @@ }, { "id": "Q8BK4VN3LC", - "explanation": "", "learningObjectives": ["081.01.02.06.02"], + "explanation": "", "variants": { "aUVcADNm": { - "id": "aUVcADNm", "type": "simple", + "id": "aUVcADNm", "question": "Skin friction drag is caused by the..", "options": [ { @@ -12672,8 +12672,8 @@ "explanation": "" }, "7twHwphr": { - "id": "7twHwphr", "type": "simple", + "id": "7twHwphr", "question": "Skin friction drag is caused by the..", "options": [ { @@ -12709,12 +12709,12 @@ }, { "id": "Q8D9MSFSP9", - "explanation": "", "learningObjectives": ["081.01", "081.05"], + "explanation": "", "variants": { "mtfhm9jN": { - "id": "mtfhm9jN", "type": "simple", + "id": "mtfhm9jN", "question": "When roll spoilers are extended, the part of the wing on which they are mounted:", "options": [ { @@ -12755,12 +12755,12 @@ }, { "id": "Q8E71S8ER1", - "explanation": "", "learningObjectives": ["081.01.01.01.03"], + "explanation": "", "variants": { "7ggoaYEO": { - "id": "7ggoaYEO", "type": "simple", + "id": "7ggoaYEO", "question": "Newtons second law of motion states that:", "options": [ { @@ -12796,12 +12796,12 @@ }, { "id": "Q8ECJQHJCH", - "explanation": "", "learningObjectives": ["081.01.01.01.01"], + "explanation": "", "variants": { "27fMdMMw": { - "id": "27fMdMMw", "type": "simple", + "id": "27fMdMMw", "question": "The SI unit of measurement for pressure is:", "options": [ { @@ -12837,12 +12837,12 @@ }, { "id": "Q8FY4WZUJ8", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "eGgtOKo9": { - "id": "eGgtOKo9", "type": "simple", + "id": "eGgtOKo9", "question": "Consider an aerofoil with a positive camber and a positive angle of attack. At which location will the highest flow velocities occur?", "options": [ { @@ -12875,8 +12875,8 @@ "explanation": "" }, "mVTrw7Ja": { - "id": "mVTrw7Ja", "type": "simple", + "id": "mVTrw7Ja", "question": "Consider an aerofoil with a certain camber and a positive angle of attack. At which location will the highest flow velocities occur?", "options": [ { @@ -12912,12 +12912,12 @@ }, { "id": "Q8GN3DYHRN", - "explanation": "", "learningObjectives": ["081.01.10.01.03"], + "explanation": "", "variants": { "TiaxMu9R": { - "id": "TiaxMu9R", "type": "simple", + "id": "TiaxMu9R", "question": "Refer to figure. \n How will the graph change if spoilers are deployed?", "options": [ { @@ -12953,12 +12953,12 @@ }, { "id": "Q8HQLRT021", - "explanation": "", "learningObjectives": ["081.01.03.03.02"], + "explanation": "", "variants": { "b0RlLKoA": { - "id": "b0RlLKoA", "type": "simple", + "id": "b0RlLKoA", "question": " \n Assuming all bodies have the same cross-sectional area and are in motion, place these bodies in order of decreasing pressure drag.The correct answer is:", "options": [ { @@ -12991,8 +12991,8 @@ "explanation": "" }, "OtAWW0pS": { - "id": "OtAWW0pS", "type": "simple", + "id": "OtAWW0pS", "question": " \n Assuming all bodies have the same cross-sectional area and are in motion, place these bodies in order of increasing pressure drag.The correct answer is:", "options": [ { @@ -13028,12 +13028,12 @@ }, { "id": "Q8IZFV3RHB", - "explanation": "", "learningObjectives": ["081.01.05.07.03"], + "explanation": "", "variants": { "I9ZmC8ZR": { - "id": "I9ZmC8ZR", "type": "simple", + "id": "I9ZmC8ZR", "question": "Refer to figure. \n If an Aeroplane is flying such that the speed stability is negative, the CAS is in the region of the curve where...", "options": [ { @@ -13069,12 +13069,12 @@ }, { "id": "QUXTSIVKDD", - "explanation": "", "learningObjectives": ["081.01.02.06.02"], + "explanation": "", "variants": { "causVH7A": { - "id": "causVH7A", "type": "simple", + "id": "causVH7A", "question": "The factor(s) causing skin friction drag is/are...", "options": [ { @@ -13110,12 +13110,12 @@ }, { "id": "Q8QAEKFUZ1", - "explanation": "", "learningObjectives": ["081.01.06.01.02"], + "explanation": "", "variants": { "Q0dg3Sfs": { - "id": "Q0dg3Sfs", "type": "simple", + "id": "Q0dg3Sfs", "question": "Which statements, about an aeroplane leaving ground effect at constant angle of attack, is correct?\n1) The lift coefficient C~L~ remains constant.\n2) The induced drag coefficient C~Di~ increases.", "options": [ { @@ -13151,12 +13151,12 @@ }, { "id": "Q8R64LU9A1", - "explanation": "", "learningObjectives": ["081.01.04.02.03"], + "explanation": "", "variants": { "n7KWwoaE": { - "id": "n7KWwoaE", "type": "simple", + "id": "n7KWwoaE", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n\n1. Assuming no flow separation, the strength of wing tip vortices decreases as the angle of attack increases.\n\n2. The strength of wing tip vortices decreases as the aspect ratio increases.", "options": [ { @@ -13208,8 +13208,8 @@ "explanation": "" }, "CHdb5nrp": { - "id": "CHdb5nrp", "type": "simple", + "id": "CHdb5nrp", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n\n1. Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack increases.\n\n2. The strength of wing tip vortices decreases as the aspect ratio decreases.", "options": [ { @@ -13242,8 +13242,8 @@ "explanation": "" }, "CZ24w9Ru": { - "id": "CZ24w9Ru", "type": "simple", + "id": "CZ24w9Ru", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n\n1. Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack decreases.\n\n2. The strength of wing tip vortices decreases as the aspect ratio increases.", "options": [ { @@ -13276,8 +13276,8 @@ "explanation": "" }, "5LzCrcDK": { - "id": "5LzCrcDK", "type": "simple", + "id": "5LzCrcDK", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n\n1. Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack decreases.\n\n2. The strength of wing tip vortices increases as the aspect ratio decreases.", "options": [ { @@ -13310,8 +13310,8 @@ "explanation": "" }, "YPB58UCV": { - "id": "YPB58UCV", "type": "simple", + "id": "YPB58UCV", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n\n1. Assuming no flow separation, the strength of wing tip vortices decreases as the angle of attack increases.\n\n2. The strength of wing tip vortices increases as the aspect ratio decreases.", "options": [ { @@ -13344,8 +13344,8 @@ "explanation": "" }, "yd7P3GzB": { - "id": "yd7P3GzB", "type": "simple", + "id": "yd7P3GzB", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n\n1. Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack decreases.\n\n2. The strength of wing tip vortices increases as the aspect ratio increases.", "options": [ { @@ -13378,8 +13378,8 @@ "explanation": "" }, "E6lHHBUi": { - "id": "E6lHHBUi", "type": "simple", + "id": "E6lHHBUi", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n\n1. Assuming no flow separation, the strength of wing tip vortices decreases as the angle of attack increases.\n\n2. The strength of wing tip vortices increases as the aspect ratio increases.", "options": [ { @@ -13412,8 +13412,8 @@ "explanation": "" }, "pFyOu74K": { - "id": "pFyOu74K", "type": "simple", + "id": "pFyOu74K", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n\n1. Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack increases.\n\n2. The strength of wing tip vortices decreases as the aspect ratio increases.", "options": [ { @@ -13446,8 +13446,8 @@ "explanation": "" }, "ok5nWBsF": { - "id": "ok5nWBsF", "type": "simple", + "id": "ok5nWBsF", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n\n1. Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack increases.\n\n2. The strength of wing tip vortices increases as the aspect ratio decreases.", "options": [ { @@ -13480,8 +13480,8 @@ "explanation": "" }, "613GyjWI": { - "id": "613GyjWI", "type": "simple", + "id": "613GyjWI", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n\n1. Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack increases.\n\n2. The strength of wing tip vortices increases as the aspect ratio increases.", "options": [ { @@ -13514,8 +13514,8 @@ "explanation": "" }, "V7AhnXhT": { - "id": "V7AhnXhT", "type": "simple", + "id": "V7AhnXhT", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n\n1. Assuming no flow separation, the strength of wing tip vortices decreases as the angle of attack decreases.\n\n2. The strength of wing tip vortices decreases as the aspect ratio increases.", "options": [ { @@ -13548,8 +13548,8 @@ "explanation": "" }, "l6R0eksj": { - "id": "l6R0eksj", "type": "simple", + "id": "l6R0eksj", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n\n1. Assuming no flow separation, the strength of wing tip vortices decreases as the angle of attack increases.\n\n2. The strength of wing tip vortices decreases as the aspect ratio decreases.", "options": [ { @@ -13582,8 +13582,8 @@ "explanation": "" }, "N9a7zxHf": { - "id": "N9a7zxHf", "type": "simple", + "id": "N9a7zxHf", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n\n1. Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack decreases.\n\n2. The strength of wing tip vortices decreases as the aspect ratio decreases.", "options": [ { @@ -13616,8 +13616,8 @@ "explanation": "" }, "uCECVfxN": { - "id": "uCECVfxN", "type": "simple", + "id": "uCECVfxN", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n\n1. Assuming no flow separation, the strength of wing tip vortices decreases as the angle of attack decreases.\n\n2. The strength of wing tip vortices increases as the aspect ratio decreases.", "options": [ { @@ -13650,8 +13650,8 @@ "explanation": "" }, "Io1HtVZl": { - "id": "Io1HtVZl", "type": "simple", + "id": "Io1HtVZl", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n\n1. Assuming no flow separation, the strength of wing tip vortices decreases as the angle of attack decreases.\n\n2. The strength of wing tip vortices decreases as the aspect ratio decreases.", "options": [ { @@ -13687,12 +13687,12 @@ }, { "id": "QBKH1CESPM", - "explanation": "", "learningObjectives": ["081.01.12.02.01"], + "explanation": "", "variants": { "bax3vaTA": { - "id": "bax3vaTA", "type": "simple", + "id": "bax3vaTA", "question": "What is the effect on an aeroplane's characteristics of extending Fowler flaps to their fully extended position?", "options": [ { @@ -13733,12 +13733,12 @@ }, { "id": "Q8RM3U9MQP", - "explanation": "", "learningObjectives": ["081.01.09.02.02"], + "explanation": "", "variants": { "SXFOtqv8": { - "id": "SXFOtqv8", "type": "simple", + "id": "SXFOtqv8", "question": "Slat extension", "options": [ { @@ -13774,12 +13774,12 @@ }, { "id": "Q8SK36A72S", - "explanation": "", "learningObjectives": ["081.01.09.01.06"], + "explanation": "", "variants": { "jt9LAtcL": { - "id": "jt9LAtcL", "type": "simple", + "id": "jt9LAtcL", "question": "When flaps are retracted at constant angle of attack the lift coefficient will:", "options": [ { @@ -13822,12 +13822,12 @@ }, { "id": "Q8SOB3H225", - "explanation": "", "learningObjectives": ["081.01.03.02.02"], + "explanation": "", "variants": { "rNuKIDPg": { - "id": "rNuKIDPg", "type": "simple", + "id": "rNuKIDPg", "question": "The lift coefficient C~L~ versus angle of attack curve of a symmetrical aerofoil section intersects the horizontal axis of the graph:", "options": [ { @@ -13867,8 +13867,8 @@ "explanation": "" }, "lKI26945": { - "id": "lKI26945", "type": "simple", + "id": "lKI26945", "question": "The lift coefficient C~L~ versus angle of attack curve of a symmetrical aerofoil section intersects the vertical axis of the graph:", "options": [ { @@ -13901,8 +13901,8 @@ "explanation": "" }, "27ov3KC0": { - "id": "27ov3KC0", "type": "simple", + "id": "27ov3KC0", "question": "The lift coefficient C~L~ versus angle of attack curve of a positive cambered aerofoil section intersects the vertical axis of the graph:", "options": [ { @@ -13935,8 +13935,8 @@ "explanation": "" }, "siDhqYEu": { - "id": "siDhqYEu", "type": "simple", + "id": "siDhqYEu", "question": "The lift coefficient C~L~ versus angle of attack curve of a negatively cambered aerofoil section intersects the horizontal axis of the graph:", "options": [ { @@ -13972,12 +13972,12 @@ }, { "id": "Q8TQJC47VG", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "WGtonTNU": { - "id": "WGtonTNU", "type": "simple", + "id": "WGtonTNU", "question": "The point, where the single resultant aerodynamic force acts on an aerofoil, is called:", "options": [ { @@ -14013,12 +14013,12 @@ }, { "id": "Q8V0ZXZF7C", - "explanation": "", "learningObjectives": ["081.01.09.01.09"], + "explanation": "", "variants": { "9BBDvzsp": { - "id": "9BBDvzsp", "type": "simple", + "id": "9BBDvzsp", "question": "While performing an obstacle limited take-off, you inadvertently set a lower take-off flap setting (less flap) than the calculated and required. Compared to a take-off at the correct flap setting , the aircraft will pass the departure end of the runway at...", "options": [ { @@ -14054,12 +14054,12 @@ }, { "id": "Q8VD6C7J54", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "lUBYk9Bt": { - "id": "lUBYk9Bt", "type": "simple", + "id": "lUBYk9Bt", "question": "Which one of the following statements about the lift-to-drag ratio in straight and level flight is correct?", "options": [ { @@ -14100,12 +14100,12 @@ }, { "id": "Q8VJ41MBWI", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "AgrqoW07": { - "id": "AgrqoW07", "type": "simple", + "id": "AgrqoW07", "question": "Whilst maintaining straight and level flight with a lift coefficient CL = 1, what will be the new approximate value of CL after the speed is increased by 41%?", "options": [ { @@ -14138,8 +14138,8 @@ "explanation": "" }, "PdnXhNqn": { - "id": "PdnXhNqn", "type": "simple", + "id": "PdnXhNqn", "question": "Whilst maintaining straight and level flight with a lift coefficient CL = 1, what will be the new approximate value of CL after the speed is increased by 41 %?", "options": [ { @@ -14175,12 +14175,12 @@ }, { "id": "Q8XY13LIPA", - "explanation": "", "learningObjectives": ["081.01.02.01.02"], + "explanation": "", "variants": { "6LbMgsdf": { - "id": "6LbMgsdf", "type": "simple", + "id": "6LbMgsdf", "question": "In a stationary subsonic streamline flow pattern, if the streamlines converge, in this part of the pattern, the static pressure will ___ and the velocity will ___.", "options": [ { @@ -14216,12 +14216,12 @@ }, { "id": "Q8YQ96HHP0", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "uR6gFJ1j": { - "id": "uR6gFJ1j", "type": "simple", + "id": "uR6gFJ1j", "question": "The main effect of leading-edge slats is to...", "options": [ { @@ -14257,12 +14257,12 @@ }, { "id": "QWUA6L94QI", - "explanation": "", "learningObjectives": ["081.01.01.05.05"], + "explanation": "", "variants": { "hkwUalNU": { - "id": "hkwUalNU", "type": "simple", + "id": "hkwUalNU", "question": "Assuming zero wing twist, the wing planform that gives the highest local lift coefficient at the wing root is:", "options": [ { @@ -14300,8 +14300,8 @@ "explanation": "" }, "v3XJwDfF": { - "id": "v3XJwDfF", "type": "simple", + "id": "v3XJwDfF", "question": "Assuming zero wing twist, the wing planform that gives the highest local lift coefficient at the wing root is:", "options": [ { @@ -14337,12 +14337,12 @@ }, { "id": "QH3ARKHVSJ", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "Y15aFMV4": { - "id": "Y15aFMV4", "type": "simple", + "id": "Y15aFMV4", "question": "The location of the centre of pressure of a positively cambered aerofoil section at increasing angle of attack will:", "options": [ { @@ -14380,8 +14380,8 @@ "explanation": "" }, "InUpL3wi": { - "id": "InUpL3wi", "type": "simple", + "id": "InUpL3wi", "question": "The location of the centre of pressure of a positively cambered aerofoil section at increasing angle of attack will:", "options": [ { @@ -14417,12 +14417,12 @@ }, { "id": "Q96GK6XUZW", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "dblSAq3o": { - "id": "dblSAq3o", "type": "simple", + "id": "dblSAq3o", "question": "Regarding a symmetrical aerofoil section, which statement is correct?The Lift Coefficient is only..", "options": [ { @@ -14458,12 +14458,12 @@ }, { "id": "Q96JZHVXTF", - "explanation": "", "learningObjectives": ["081.01.02.09.02"], + "explanation": "", "variants": { "kGF46zbP": { - "id": "kGF46zbP", "type": "simple", + "id": "kGF46zbP", "question": "Refer to a CL vs AoA curve for a non-symmetrical wing, where CL line is the Y-axis and AOA line is the X-axis.\nWhere do we find CL~MAX~?", "options": [ { @@ -14499,12 +14499,12 @@ }, { "id": "QB8RSJZKOP", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "V5uWLHAa": { - "id": "V5uWLHAa", "type": "simple", + "id": "V5uWLHAa", "question": "Whilst maintaining straight and level flight with a lift coefficient CL=1, what will be the new value of CL after the speed has doubled?", "options": [ { @@ -14545,12 +14545,12 @@ }, { "id": "Q98832BPBC", - "explanation": "", "learningObjectives": ["081.01.04.02.03"], + "explanation": "", "variants": { "kytx4ASg": { - "id": "kytx4ASg", "type": "simple", + "id": "kytx4ASg", "question": "What is correct about wingtip vortices? They are...", "options": [ { @@ -14586,12 +14586,12 @@ }, { "id": "Q99AE4NTCZ", - "explanation": "", "learningObjectives": ["081.01", "081.06"], + "explanation": "", "variants": { "XHxj6R8I": { - "id": "XHxj6R8I", "type": "simple", + "id": "XHxj6R8I", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly decreases the speed by 40 kt \nAssuming the angle of attack remains constant, the load factor will initially", "options": [ { @@ -14624,8 +14624,8 @@ "explanation": "" }, "m2F9SZL4": { - "id": "m2F9SZL4", "type": "simple", + "id": "m2F9SZL4", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly increases the speed by 40 kt\n \n Assuming the angle of attack remains constant, the load factor will initially", "options": [ { @@ -14658,8 +14658,8 @@ "explanation": "" }, "rr7SsdPM": { - "id": "rr7SsdPM", "type": "simple", + "id": "rr7SsdPM", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly increases the speed by 60 kt\nAssuming the angle of attack remains constant, the load factor will initially", "options": [ { @@ -14692,8 +14692,8 @@ "explanation": "" }, "yi8HEkZQ": { - "id": "yi8HEkZQ", "type": "simple", + "id": "yi8HEkZQ", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly decreases the speed by 60 kt \nAssuming the angle of attack remains constant, the load factor will initially", "options": [ { @@ -14726,8 +14726,8 @@ "explanation": "" }, "2qhEMvtG": { - "id": "2qhEMvtG", "type": "simple", + "id": "2qhEMvtG", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly increases the speed by 80 kt\n \n Assuming the angle of attack remains constant, the load factor will initially", "options": [ { @@ -14760,8 +14760,8 @@ "explanation": "" }, "EFHAnqOc": { - "id": "EFHAnqOc", "type": "simple", + "id": "EFHAnqOc", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly decreases the speed by 80 kt\n Assuming the angle of attack remains constant, the load factor will initially", "options": [ { @@ -14794,8 +14794,8 @@ "explanation": "" }, "JHqt7LyO": { - "id": "JHqt7LyO", "type": "simple", + "id": "JHqt7LyO", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly decreases the speed by 20 kt \nAssuming the angle of attack remains constant, the load factor will initially", "options": [ { @@ -14828,8 +14828,8 @@ "explanation": "" }, "JdbTsUDX": { - "id": "JdbTsUDX", "type": "simple", + "id": "JdbTsUDX", "question": "An aeroplane flying at 100 kt in straight and level flight is subjected to a disturbance that suddenly increases the speed by 20 kt\n Assuming the angle of attack remains constant, the load factor will initially", "options": [ { @@ -14862,8 +14862,8 @@ "explanation": "" }, "QIO1gFPv": { - "id": "QIO1gFPv", "type": "simple", + "id": "QIO1gFPv", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly increases the speed by 20 kt. Assuming the angle of attack remains constant, the load factor will initially", "options": [ { @@ -14896,8 +14896,8 @@ "explanation": "" }, "YIROEF4N": { - "id": "YIROEF4N", "type": "simple", + "id": "YIROEF4N", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly increases the speed by 10 kt\n \n Assuming the angle of attack remains constant, the load factor will initially", "options": [ { @@ -14930,8 +14930,8 @@ "explanation": "" }, "vtqDgcVq": { - "id": "vtqDgcVq", "type": "simple", + "id": "vtqDgcVq", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly decreases the speed by 10 kt\nAssuming the angle of attack remains constant, the load factor will initially", "options": [ { @@ -14964,8 +14964,8 @@ "explanation": "" }, "vvuYxBcz": { - "id": "vvuYxBcz", "type": "simple", + "id": "vvuYxBcz", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly increases the speed by 100 kt \nAssuming the angle of attack remains constant, the load factor will initially", "options": [ { @@ -14998,8 +14998,8 @@ "explanation": "" }, "th9fzVU7": { - "id": "th9fzVU7", "type": "simple", + "id": "th9fzVU7", "question": "An aeroplane flying at 200 kt in straight and level flight is subjected to a disturbance that suddenly decreases the speed by 100 kt \nAssuming the angle of attack remains constant, the load factor will initially", "options": [ { @@ -15035,12 +15035,12 @@ }, { "id": "Q9BNDURE5G", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "WQXw7wiZ": { - "id": "WQXw7wiZ", "type": "simple", + "id": "WQXw7wiZ", "question": "Which statements about induced drag are correct or incorrect?\n1) Induced drag increases as angle of attack increases.\n2) At constant load factor, induced drag decreases with increasing aeroplane mass.", "options": [ { @@ -15076,12 +15076,12 @@ }, { "id": "Q9DHH0JO4D", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "WHOIKBOB": { - "id": "WHOIKBOB", "type": "simple", + "id": "WHOIKBOB", "question": "The total reaction force on the airfoil is split between\nLift and Drag. Lift is:", "options": [ { @@ -15117,12 +15117,12 @@ }, { "id": "QC1UHSTTJN", - "explanation": "", "learningObjectives": ["081.01.09.02.07"], + "explanation": "", "variants": { "Z1cwVObc": { - "id": "Z1cwVObc", "type": "simple", + "id": "Z1cwVObc", "question": "For most jet transport aeroplanes, slat extension has:", "options": [ { @@ -15163,12 +15163,12 @@ }, { "id": "Q9IPGULJKL", - "explanation": "", "learningObjectives": ["081.01.01.02.04"], + "explanation": "", "variants": { "r5RQdsRe": { - "id": "r5RQdsRe", "type": "simple", + "id": "r5RQdsRe", "question": "The fundamental difference between the aerodynamic characteristics of two and three-dimensional flow is that, in a three-dimensional flow about a wing", "options": [ { @@ -15209,12 +15209,12 @@ }, { "id": "QDFA07YNAJ", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "JzALnreK": { - "id": "JzALnreK", "type": "simple", + "id": "JzALnreK", "question": "The induced drag increases as the..", "options": [ { @@ -15255,12 +15255,12 @@ }, { "id": "Q9MDQBH8TB", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "IjlxRhpD": { - "id": "IjlxRhpD", "type": "simple", + "id": "IjlxRhpD", "question": "In straight and level flight at a speed of 2 VS, the lift coefficient, expressed as a percentage of its maximum CLMAX, would be", "options": [ { @@ -15296,12 +15296,12 @@ }, { "id": "Q9P1BJO94A", - "explanation": "", "learningObjectives": ["081.01.09.01.08"], + "explanation": "", "variants": { "Fk6Mw5pp": { - "id": "Fk6Mw5pp", "type": "simple", + "id": "Fk6Mw5pp", "question": "A crew calculate landing speeds for a full flap landing (30⁰) but, due to distraction, omit to extend flaps further than the approach setting (15⁰). Which of the following statements is correct assuming the correct glidepath was flown to touchdown?", "options": [ { @@ -15337,12 +15337,12 @@ }, { "id": "Q9Q7SPV8PD", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "T0miqXVx": { - "id": "T0miqXVx", "type": "simple", + "id": "T0miqXVx", "question": "Regarding a positively cambered aerofoil section, which statement is correct?\n\n1. The angle of attack has a negative value when the lift coefficient equals zero.\n\n2. A nose down pitching moment exists when the lift coefficient equals zero.", "options": [ { @@ -15381,8 +15381,8 @@ "explanation": "" }, "mKFUOuv5": { - "id": "mKFUOuv5", "type": "simple", + "id": "mKFUOuv5", "question": "Regarding a positively cambered aerofoil section, which statement is correct?\n\nI. The angle of attack has a positive value when the lift coefficient equals zero. \nII. A nose down pitching moment exists when the lift coefficient equals zero.", "options": [ { @@ -15418,12 +15418,12 @@ }, { "id": "Q9QEYDZHTX", - "explanation": "", "learningObjectives": ["081.01.04.03.04"], + "explanation": "", "variants": { "qCGQeJHe": { - "id": "qCGQeJHe", "type": "simple", + "id": "qCGQeJHe", "question": "Flying at 400Kts IAS at sea level, the value of drag is 780N.\n What would be the value of drag at 6000ft, if the IAS is maintained, and all other factors remain constant?", "options": [ { @@ -15459,12 +15459,12 @@ }, { "id": "Q9TBT5T41K", - "explanation": "", "learningObjectives": ["081.01.01.04.07"], + "explanation": "", "variants": { "BRYvBiYy": { - "id": "BRYvBiYy", "type": "simple", + "id": "BRYvBiYy", "question": "The lift coefficient (C~L~) is a function of which of the following?\n1) Density.\n2) Pressure.\n3) Temperature.\n4) Camber of the aerofoil section.\n5) Angle of attack of the aerofoil section.\nPlease choose the answer which combines all correct statements:", "options": [ { @@ -15500,12 +15500,12 @@ }, { "id": "Q9TTF7OMBB", - "explanation": "", "learningObjectives": ["081.01.09.01.05"], + "explanation": "", "variants": { "31dgOaMT": { - "id": "31dgOaMT", "type": "simple", + "id": "31dgOaMT", "question": "Refer to figure. \n Which of the augmentations in the annex will increase the wings C~L~?", "options": [ { @@ -15541,12 +15541,12 @@ }, { "id": "Q9X2VW7LDH", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "mG439r7H": { - "id": "mG439r7H", "type": "simple", + "id": "mG439r7H", "question": "An aerospace company needs to attach a testing device to the outside of their aircraft. How can the least amount of drag be achieved?", "options": [ { @@ -15582,12 +15582,12 @@ }, { "id": "Q9ZCVCD62Z", - "explanation": "", "learningObjectives": ["081.01.01.01.01"], + "explanation": "", "variants": { "Px1ntjCX": { - "id": "Px1ntjCX", "type": "simple", + "id": "Px1ntjCX", "question": "The SI unit of measurement for density is", "options": [ { @@ -15623,12 +15623,12 @@ }, { "id": "QA256RKUSH", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "eoHKMjd8": { - "id": "eoHKMjd8", "type": "simple", + "id": "eoHKMjd8", "question": "Minimum drag of an aeroplane in straight and level flight occurs at the:", "options": [ { @@ -15666,8 +15666,8 @@ "explanation": "" }, "XqhSR9m6": { - "id": "XqhSR9m6", "type": "simple", + "id": "XqhSR9m6", "question": "Minimum drag of an aeroplane in straight and level flight occurs at the:", "options": [ { @@ -15703,12 +15703,12 @@ }, { "id": "QA4JMMN0AE", - "explanation": "", "learningObjectives": ["081.01.06.01.02"], + "explanation": "", "variants": { "BHwuVA4z": { - "id": "BHwuVA4z", "type": "simple", + "id": "BHwuVA4z", "question": "Considering the following information, at which height from the ground is induced drag felt the most?\n32 ft AAL \nWingspan: 20 metres", "options": [ { @@ -15744,12 +15744,12 @@ }, { "id": "QA75UTDI6M", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "k2GBqm0T": { - "id": "k2GBqm0T", "type": "simple", + "id": "k2GBqm0T", "question": "An aircraft accelerates from Vs to 1.8Vs in level flight. If the value of the coefficient of lift at Vs is 100%, what will be its value at the higher speed?", "options": [ { @@ -15785,12 +15785,12 @@ }, { "id": "QA8IF3IQLL", - "explanation": "", "learningObjectives": ["081.01.04.03.03"], + "explanation": "", "variants": { "IVZu4tsU": { - "id": "IVZu4tsU", "type": "simple", + "id": "IVZu4tsU", "question": "In what way do induced drag and parasite drag alter with increasing speed in straight and level flight?", "options": [ { @@ -15826,12 +15826,12 @@ }, { "id": "QAAQSWNMFD", - "explanation": "", "learningObjectives": ["081.01.01.05.03"], + "explanation": "", "variants": { "w69opujE": { - "id": "w69opujE", "type": "simple", + "id": "w69opujE", "question": "The taper ratio of a wing is the ratio between the..", "options": [ { @@ -15872,12 +15872,12 @@ }, { "id": "QAGVJC25ZS", - "explanation": "", "learningObjectives": ["081.01.05.07.02"], + "explanation": "", "variants": { "U2FvA784": { - "id": "U2FvA784", "type": "simple", + "id": "U2FvA784", "question": "For a given aircraft at a given height and therefore air\ndensity, doubling the TAS will increase the Parasite\nDrag:", "options": [ { @@ -15913,12 +15913,12 @@ }, { "id": "QAI7RFEKJ0", - "explanation": "", "learningObjectives": ["081.01", "081.03"], + "explanation": "", "variants": { "2tS2yQJp": { - "id": "2tS2yQJp", "type": "simple", + "id": "2tS2yQJp", "question": "A laminar boundary layer is a layer, in which:", "options": [ { @@ -15957,8 +15957,8 @@ "explanation": "" }, "RFK9G3My": { - "id": "RFK9G3My", "type": "simple", + "id": "RFK9G3My", "question": "A laminar boundary layer is a layer, in which:", "options": [ { @@ -15994,12 +15994,12 @@ }, { "id": "QAIV1GHKD3", - "explanation": "", "learningObjectives": ["081.01.01.01.09"], + "explanation": "", "variants": { "0N0sw0ZO": { - "id": "0N0sw0ZO", "type": "simple", + "id": "0N0sw0ZO", "question": "Which of the following statements about Bernoulli's Theorem is correct?\n(Ps: Static Pressure, Pd: Dynamic Pressure, Ptot: Total Pressure)", "options": [ { @@ -16035,12 +16035,12 @@ }, { "id": "QAK7QQFYFP", - "explanation": "", "learningObjectives": ["081.01.03.03.02"], + "explanation": "", "variants": { "jBW4WBnT": { - "id": "jBW4WBnT", "type": "simple", + "id": "jBW4WBnT", "question": "(For this question use the image in the annex). Assuming all bodies have the same cross-sectional area and are in motion, which body will have the lowest pressure drag?", "options": [ { @@ -16076,12 +16076,12 @@ }, { "id": "QAL90UFDOK", - "explanation": "", "learningObjectives": ["081.01.04.03.02"], + "explanation": "", "variants": { "m1FpjFxn": { - "id": "m1FpjFxn", "type": "simple", + "id": "m1FpjFxn", "question": "Assuming constant speed induced drag is:", "options": [ { @@ -16117,12 +16117,12 @@ }, { "id": "QMN7YRI0U4", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "ZYx5C4fN": { - "id": "ZYx5C4fN", "type": "simple", + "id": "ZYx5C4fN", "question": "Ground effect has the following influence on the landing distance:", "options": [ { @@ -16163,12 +16163,12 @@ }, { "id": "QAP4257YO9", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "hUzTqW1C": { - "id": "hUzTqW1C", "type": "simple", + "id": "hUzTqW1C", "question": "Induced drag may be reduced by:", "options": [ { @@ -16201,8 +16201,8 @@ "explanation": "" }, "SIJgJBUX": { - "id": "SIJgJBUX", "type": "simple", + "id": "SIJgJBUX", "question": "Induced drag may be reduced by:", "options": [ { @@ -16238,12 +16238,12 @@ }, { "id": "QAPRGMCPN6", - "explanation": "", "learningObjectives": ["081.01.01.01.09"], + "explanation": "", "variants": { "dfwhtMDp": { - "id": "dfwhtMDp", "type": "simple", + "id": "dfwhtMDp", "question": "Given: pstat = static pressure; q = dynamic pressure; ptot = total pressure. In a convergent tube with an incompressible subsonic airflow, what pressure changes will occur?", "options": [ { @@ -16279,12 +16279,12 @@ }, { "id": "QAPSF4G27Z", - "explanation": "", "learningObjectives": ["081.01.06.01.01"], + "explanation": "", "variants": { "czxIs8lR": { - "id": "czxIs8lR", "type": "simple", + "id": "czxIs8lR", "question": "As an aeroplane slows down during the approach, the wing tip vortices and downwash will vary in intensity. How does this affect the induced angle of attack? Induced angle of attack will...", "options": [ { @@ -16320,12 +16320,12 @@ }, { "id": "QAQS65QAR8", - "explanation": "", "learningObjectives": ["081.01.02.06.02"], + "explanation": "", "variants": { "50EQBxbj": { - "id": "50EQBxbj", "type": "simple", + "id": "50EQBxbj", "question": "Friction drag is caused by the...", "options": [ { @@ -16361,12 +16361,12 @@ }, { "id": "QATB8YBKSR", - "explanation": "", "learningObjectives": ["081.01.06.01.01"], + "explanation": "", "variants": { "BQbdqeIH": { - "id": "BQbdqeIH", "type": "simple", + "id": "BQbdqeIH", "question": "Which statements about an aeroplane leaving ground effect are correct or incorrect?\n1) The downwash angle decreases.\n2) The induced angle of attack decreases.", "options": [ { @@ -16406,8 +16406,8 @@ "explanation": "" }, "rUEtx1Fh": { - "id": "rUEtx1Fh", "type": "simple", + "id": "rUEtx1Fh", "question": "Which statements about an aeroplane leaving ground effect are correct or incorrect?\n1) The downwash angle decreases.\n2) The induced angle of attack increases.", "options": [ { @@ -16440,8 +16440,8 @@ "explanation": "" }, "1BENWoLW": { - "id": "1BENWoLW", "type": "simple", + "id": "1BENWoLW", "question": "Which statements about an aeroplane entering ground effect are correct or incorrect?\n1) The downwash angle decreases.\n2) The induced angle of attack decreases.", "options": [ { @@ -16477,12 +16477,12 @@ }, { "id": "QLCBYF6WV8", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "PHkWrPey": { - "id": "PHkWrPey", "type": "simple", + "id": "PHkWrPey", "question": "The main function of a trailing edge flap is to:", "options": [ { @@ -16523,12 +16523,12 @@ }, { "id": "QAXF0WCG4H", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "gyPddyK8": { - "id": "gyPddyK8", "type": "simple", + "id": "gyPddyK8", "question": "Which of the following are most effective at reducing induced drag?", "options": [ { @@ -16561,8 +16561,8 @@ "explanation": "" }, "QcJbbAVC": { - "id": "QcJbbAVC", "type": "simple", + "id": "QcJbbAVC", "question": "Which of the following are most effective at reducing induced drag?", "options": [ { @@ -16598,12 +16598,12 @@ }, { "id": "QAY9ZAZ1UD", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "DLe68oUR": { - "id": "DLe68oUR", "type": "simple", + "id": "DLe68oUR", "question": "An aeroplane has the following flap settings: 0°, 15°, 30° and 45°. Slats can also be selected. Which of the following selections will most adversely affect the C~L~/C~D~ ratio?", "options": [ { @@ -16644,12 +16644,12 @@ }, { "id": "QB5BQG0AEI", - "explanation": "", "learningObjectives": ["081.01.06.01.03"], + "explanation": "", "variants": { "gTA8808G": { - "id": "gTA8808G", "type": "simple", + "id": "gTA8808G", "question": "Ground effect during the flare will:", "options": [ { @@ -16685,12 +16685,12 @@ }, { "id": "QYBIBR5RVW", - "explanation": "", "learningObjectives": ["081.01.04.03.03"], + "explanation": "", "variants": { "b7a6Z7mx": { - "id": "b7a6Z7mx", "type": "simple", + "id": "b7a6Z7mx", "question": "How does the total drag change, in straight and level flight at constant mass, as speed is increased from the stall speed (VS) to maximum IAS (VNE or VMO)?", "options": [ { @@ -16731,12 +16731,12 @@ }, { "id": "QB87F7DQPX", - "explanation": "", "learningObjectives": ["081.01.01.01.09"], + "explanation": "", "variants": { "sVkV9VKU": { - "id": "sVkV9VKU", "type": "simple", + "id": "sVkV9VKU", "question": "Total pressure is (rho = density)?", "options": [ { @@ -16772,12 +16772,12 @@ }, { "id": "QB8U5O2MLL", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "polGS9oy": { - "id": "polGS9oy", "type": "simple", + "id": "polGS9oy", "question": "An aeroplane flies in straight and level flight with a lift coefficient C~L~=1. What will be the new value of C~L~ after the speed has doubled, whilst still maintaining the original condition of flight?", "options": [ { @@ -16813,12 +16813,12 @@ }, { "id": "QB9I8NS6YP", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "JuMnrZMi": { - "id": "JuMnrZMi", "type": "simple", + "id": "JuMnrZMi", "question": "Refer to figure 081-44.\nWhich of the high lift devices shown on the left side, correspond(s) to the curve?", "options": [ { @@ -16854,12 +16854,12 @@ }, { "id": "QB9LGX6524", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "BonPekOZ": { - "id": "BonPekOZ", "type": "simple", + "id": "BonPekOZ", "question": "Assuming no flow separation and no compressibility effects, the location of the Centre of Pressure of a positively cambered aerofoil section", "options": [ { @@ -16895,12 +16895,12 @@ }, { "id": "QBBJ7UI29Z", - "explanation": "", "learningObjectives": ["081.01.12.01.01"], + "explanation": "", "variants": { "nPfOEMUj": { - "id": "nPfOEMUj", "type": "simple", + "id": "nPfOEMUj", "question": "While flying under icing conditions, the largest ice build-up will occur, principally, on:", "options": [ { @@ -16933,8 +16933,8 @@ "explanation": "" }, "CLyJRCBr": { - "id": "CLyJRCBr", "type": "simple", + "id": "CLyJRCBr", "question": "While flying under icing conditions, the largest ice build-up will occur, principally, on:", "options": [ { @@ -16970,12 +16970,12 @@ }, { "id": "QBBKRNVDPB", - "explanation": "", "learningObjectives": ["081.01.01.04.03"], + "explanation": "", "variants": { "HPDDfPiu": { - "id": "HPDDfPiu", "type": "simple", + "id": "HPDDfPiu", "question": "Refer to figure 081-50.\nLine 1 represents an airfoil in clean configuration. Which configuration represents line 2?", "options": [ { @@ -17011,8 +17011,8 @@ "explanation": "" }, "GMYKBTJt": { - "id": "GMYKBTJt", "type": "simple", + "id": "GMYKBTJt", "question": "Refer to figure 081-50.\nLine 1 represents an airfoil in clean configuration. Which configuration represents line 3?", "options": [ { @@ -17051,12 +17051,12 @@ }, { "id": "QBDDYBPJT1", - "explanation": "", "learningObjectives": ["081.01.12.02.01"], + "explanation": "", "variants": { "ekH1ig20": { - "id": "ekH1ig20", "type": "simple", + "id": "ekH1ig20", "question": "The drag due to an ageing airframe is identified as?", "options": [ { @@ -17092,12 +17092,12 @@ }, { "id": "QBDXVKMI1F", - "explanation": "", "learningObjectives": ["081.01.06.01.03"], + "explanation": "", "variants": { "ZLtLkC0A": { - "id": "ZLtLkC0A", "type": "simple", + "id": "ZLtLkC0A", "question": "When entering ground effect, maintaining the same coefficient of lift, CL, requires..", "options": [ { @@ -17133,12 +17133,12 @@ }, { "id": "QBEJPZ8TS5", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "QfC1FTKs": { - "id": "QfC1FTKs", "type": "simple", + "id": "QfC1FTKs", "question": "Refer to figure 081-11.\nThe high lift device shown in the figure 1 is a:", "options": [ { @@ -17179,12 +17179,12 @@ }, { "id": "QBFSAQHTGF", - "explanation": "", "learningObjectives": ["081.01.01.04.02"], + "explanation": "", "variants": { "869SxH58": { - "id": "869SxH58", "type": "simple", + "id": "869SxH58", "question": "Trailing edge flaps once extended:", "options": [ { @@ -17222,8 +17222,8 @@ "explanation": "" }, "J6Yfldrz": { - "id": "J6Yfldrz", "type": "simple", + "id": "J6Yfldrz", "question": "Trailing edge flaps once extended:", "options": [ { @@ -17259,12 +17259,12 @@ }, { "id": "QBM2VE1M25", - "explanation": "", "learningObjectives": ["081.01.01.04.03"], + "explanation": "", "variants": { "29CWRBvY": { - "id": "29CWRBvY", "type": "simple", + "id": "29CWRBvY", "question": "The polar curve of an aerofoil is a graphic relation between:", "options": [ { @@ -17304,8 +17304,8 @@ "explanation": "" }, "FBSFoMbw": { - "id": "FBSFoMbw", "type": "simple", + "id": "FBSFoMbw", "question": "The polar curve of an aerofoil is a graphic relation between:", "options": [ { @@ -17341,12 +17341,12 @@ }, { "id": "QBMDNRZ0P4", - "explanation": "", "learningObjectives": ["081.01.01.01.17"], + "explanation": "", "variants": { "eyymEW83": { - "id": "eyymEW83", "type": "simple", + "id": "eyymEW83", "question": "The CAS is the IAS corrected for:", "options": [ { @@ -17382,12 +17382,12 @@ }, { "id": "QBMV1F6G9G", - "explanation": "", "learningObjectives": ["081.01.03.03.01"], + "explanation": "", "variants": { "TwG7SPTX": { - "id": "TwG7SPTX", "type": "simple", + "id": "TwG7SPTX", "question": "The total drag of an aerofoil in two dimensional flow comprises:", "options": [ { @@ -17428,12 +17428,12 @@ }, { "id": "QZ4D6VEDP3", - "explanation": "", "learningObjectives": ["081.01.04.03.05"], + "explanation": "", "variants": { "6Rbc07eH": { - "id": "6Rbc07eH", "type": "simple", + "id": "6Rbc07eH", "question": "Which type of aeroplane will experience a larger decrease in induced drag at heights between ground level and a wingspan?", "options": [ { @@ -17469,12 +17469,12 @@ }, { "id": "QBSETUG8PZ", - "explanation": "", "learningObjectives": ["081.01.09.01.06"], + "explanation": "", "variants": { "sYO8m573": { - "id": "sYO8m573", "type": "simple", + "id": "sYO8m573", "question": "When deploying the flaps the effective angle of attack", "options": [ { @@ -17510,12 +17510,12 @@ }, { "id": "QBU4HNXI99", - "explanation": "", "learningObjectives": ["081.01.01.01.01"], + "explanation": "", "variants": { "A0cPo0yt": { - "id": "A0cPo0yt", "type": "simple", + "id": "A0cPo0yt", "question": "What SI unit is used for power?", "options": [ { @@ -17551,12 +17551,12 @@ }, { "id": "QBUH2QEMI8", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "bQrg1iiY": { - "id": "bQrg1iiY", "type": "simple", + "id": "bQrg1iiY", "question": "The Center of Pressure of an aerofoil section:", "options": [ { @@ -17592,12 +17592,12 @@ }, { "id": "QBXC5WRAUJ", - "explanation": "", "learningObjectives": ["081.01.10.01.02"], + "explanation": "", "variants": { "3kUXo87Z": { - "id": "3kUXo87Z", "type": "simple", + "id": "3kUXo87Z", "question": "When extending spoilers, what happens to the angle of attack and the margin to stall?", "options": [ { @@ -17633,12 +17633,12 @@ }, { "id": "QBYUJJT5AE", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "q9TGvjqY": { - "id": "q9TGvjqY", "type": "simple", + "id": "q9TGvjqY", "question": "An aircraft is flying at 100kts with a CL of 0.35. CLmax is 1.22\nWhat is the maximum achievable load factor?", "options": [ { @@ -17674,12 +17674,12 @@ }, { "id": "QC163N0535", - "explanation": "", "learningObjectives": ["081.01.01.04.07"], + "explanation": "", "variants": { "hDP1UFTl": { - "id": "hDP1UFTl", "type": "simple", + "id": "hDP1UFTl", "question": "The angle of attack of an aerofoil section is defined as the angle between the", "options": [ { @@ -17715,12 +17715,12 @@ }, { "id": "QK11W0L1I8", - "explanation": "", "learningObjectives": ["081.01.01.03.08"], + "explanation": "", "variants": { "3u3y1aDa": { - "id": "3u3y1aDa", "type": "simple", + "id": "3u3y1aDa", "question": "An aeroplane's angle of attack can be defined as the angle between its:", "options": [ { @@ -17761,12 +17761,12 @@ }, { "id": "QC2YS6D2OQ", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "nK6XcZnZ": { - "id": "nK6XcZnZ", "type": "simple", + "id": "nK6XcZnZ", "question": "For a given airplane that is travelling at 1.4 VA. When VA decreases to 1.1. By what % has CL increased if the aircraft is to maintain straight and level flight?", "options": [ { @@ -17802,12 +17802,12 @@ }, { "id": "QC383LJL2O", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "bQKcWRKX": { - "id": "bQKcWRKX", "type": "simple", + "id": "bQKcWRKX", "question": "High lift devices are used:", "options": [ { @@ -17843,12 +17843,12 @@ }, { "id": "QORUTSGAP7", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "bwwMuhAc": { - "id": "bwwMuhAc", "type": "simple", + "id": "bwwMuhAc", "question": "Describe the airflow with regards to the induced drag...", "options": [ { @@ -17884,12 +17884,12 @@ }, { "id": "QC71GDJT38", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "TNkHqW3w": { - "id": "TNkHqW3w", "type": "simple", + "id": "TNkHqW3w", "question": "Refer to figure 081-37.\nWhat kind of high lift device is this?", "options": [ { @@ -17925,12 +17925,12 @@ }, { "id": "QC7M6KC91A", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "sC2cPVnf": { - "id": "sC2cPVnf", "type": "simple", + "id": "sC2cPVnf", "question": "Extending flaps will (1)___ the wing’s effective camber and, consequently, (2) ___ the stall speed.", "options": [ { @@ -17966,12 +17966,12 @@ }, { "id": "QC7X32QU5F", - "explanation": "", "learningObjectives": ["081.01.09.01.05"], + "explanation": "", "variants": { "eoRRi5Lx": { - "id": "eoRRi5Lx", "type": "simple", + "id": "eoRRi5Lx", "question": "Compared with the clean configuration, the angle of attack at CLMAX with trailing edge flaps extended is", "options": [ { @@ -18012,12 +18012,12 @@ }, { "id": "QC8VW3DY6W", - "explanation": "", "learningObjectives": ["081.01.04.03.04"], + "explanation": "", "variants": { "CLOGsDzU": { - "id": "CLOGsDzU", "type": "simple", + "id": "CLOGsDzU", "question": "Assuming no compressibility effects, induced drag at constant IAS is affected by:", "options": [ { @@ -18056,8 +18056,8 @@ "explanation": "" }, "wKBKjm8I": { - "id": "wKBKjm8I", "type": "simple", + "id": "wKBKjm8I", "question": "Assuming no compressibility effects, induced drag at constant IAS is affected by:", "options": [ { @@ -18093,12 +18093,12 @@ }, { "id": "QC9OMD7AZO", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "B2Cu4eVp": { - "id": "B2Cu4eVp", "type": "simple", + "id": "B2Cu4eVp", "question": "Extending flaps will ___ C~L~, ___ speed and ___ stall speed?", "options": [ { @@ -18134,12 +18134,12 @@ }, { "id": "QC9SKC4U16", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "ccre9JI5": { - "id": "ccre9JI5", "type": "simple", + "id": "ccre9JI5", "question": "Assuming no flow separation, which of these statements about the flow around an aerofoil as the angle of attack decreases are correct or incorrect?\n1) The stagnation point moves up.2) The point of lowest static pressure moves aft.", "options": [ { @@ -18175,12 +18175,12 @@ }, { "id": "QCACB7FFUV", - "explanation": "", "learningObjectives": ["081.01.01.01.01"], + "explanation": "", "variants": { "sEs7V2bg": { - "id": "sEs7V2bg", "type": "simple", + "id": "sEs7V2bg", "question": "The following unit of measurement: kgm/s^2^ is expressed in the SI-system as...", "options": [ { @@ -18213,8 +18213,8 @@ "explanation": "" }, "eW7Nrjof": { - "id": "eW7Nrjof", "type": "simple", + "id": "eW7Nrjof", "question": "The following unit of measurement: kgm/s^2^ is expressed in the SI-system as...", "options": [ { @@ -18250,12 +18250,12 @@ }, { "id": "QCDL86Q2VR", - "explanation": "", "learningObjectives": ["081.01.02.01.02"], + "explanation": "", "variants": { "dKj82J6F": { - "id": "dKj82J6F", "type": "simple", + "id": "dKj82J6F", "question": "In a convergent tube with an incompressible sub-sonic airflow, the following pressure changes will occur:\nP~S~ = static pressure\nP~DYN~ = dynamic pressure\nP~TOT~ = total pressure", "options": [ { @@ -18291,12 +18291,12 @@ }, { "id": "QCGKZ145TE", - "explanation": "", "learningObjectives": ["081.01.09.02.05"], + "explanation": "", "variants": { "spr6JJQG": { - "id": "spr6JJQG", "type": "simple", + "id": "spr6JJQG", "question": "Leading and trailing edge flaps, when compared to the clean wing:I. Increase C~LMAX~ \n II. Increase C~L~/C~D~ \n III. Decrease Critical Angle of AttackWhich of the following statements are correct?", "options": [ { @@ -18332,12 +18332,12 @@ }, { "id": "QCIH43XVOA", - "explanation": "", "learningObjectives": ["081.01.01.01.09"], + "explanation": "", "variants": { "6BRsSlw1": { - "id": "6BRsSlw1", "type": "simple", + "id": "6BRsSlw1", "question": "Total pressure is: (rho = density)", "options": [ { @@ -18370,8 +18370,8 @@ "explanation": "" }, "XMlbY9v7": { - "id": "XMlbY9v7", "type": "simple", + "id": "XMlbY9v7", "question": "Total pressure is: \n(rho = density)", "options": [ { @@ -18404,8 +18404,8 @@ "explanation": "" }, "ZqYVvl0f": { - "id": "ZqYVvl0f", "type": "simple", + "id": "ZqYVvl0f", "question": "Total pressure is: (rho = density)", "options": [ { @@ -18441,12 +18441,12 @@ }, { "id": "QCJIHGU5I9", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "wgaAZA0C": { - "id": "wgaAZA0C", "type": "simple", + "id": "wgaAZA0C", "question": "On the total drag curve the speed for minimum drag in level flight is where:", "options": [ { @@ -18482,12 +18482,12 @@ }, { "id": "QCKQEA3G2I", - "explanation": "", "learningObjectives": ["081.01.01.05.05"], + "explanation": "", "variants": { "SKhrvqfV": { - "id": "SKhrvqfV", "type": "simple", + "id": "SKhrvqfV", "question": "Winglets:", "options": [ { @@ -18523,12 +18523,12 @@ }, { "id": "QCMSPQQ8DT", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "8gE6bqJE": { - "id": "8gE6bqJE", "type": "simple", + "id": "8gE6bqJE", "question": "The point in the figure corresponding to CL for minimum horizontal flight speed is", "options": [ { @@ -18564,12 +18564,12 @@ }, { "id": "QCNGYCSE1U", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "itfKOt3Y": { - "id": "itfKOt3Y", "type": "simple", + "id": "itfKOt3Y", "question": "Considering a positively cambered aerofoil section, the pitching moment when the lift coefficient Cl=0 is:", "options": [ { @@ -18602,8 +18602,8 @@ "explanation": "" }, "vhv41TkQ": { - "id": "vhv41TkQ", "type": "simple", + "id": "vhv41TkQ", "question": "Considering a positively cambered aerofoil section, the pitching moment when the lift coefficient Cl=0 is:", "options": [ { @@ -18639,12 +18639,12 @@ }, { "id": "QCP9LXXE4Y", - "explanation": "", "learningObjectives": ["081.01.12.01.03"], + "explanation": "", "variants": { "RB1iOIQm": { - "id": "RB1iOIQm", "type": "simple", + "id": "RB1iOIQm", "question": "Its a cold day, the pilot did not do de-ice nor anti-ice the aircraft. How will ice accretion affect the aircraft performance?", "options": [ { @@ -18680,12 +18680,12 @@ }, { "id": "QCPC1IMYFP", - "explanation": "", "learningObjectives": ["081.01.02.03.01"], + "explanation": "", "variants": { "kN8jmHDh": { - "id": "kN8jmHDh", "type": "simple", + "id": "kN8jmHDh", "question": "Assuming no flow separation, when speed is increased in straight and level flight on a positively cambered aerofoil, what happens to the:\n1) centre of pressure,\n2) the magnitude of the total lift force?", "options": [ { @@ -18718,8 +18718,8 @@ "explanation": "" }, "4pOgKnKy": { - "id": "4pOgKnKy", "type": "simple", + "id": "4pOgKnKy", "question": "Assuming no flow separation, when speed is decreased in straight and level flight on a positively cambered aerofoil, what happens to the:\n1) centre of pressure,\n2) the magnitude of the total lift force?", "options": [ { @@ -18755,12 +18755,12 @@ }, { "id": "QCSXY2ND5O", - "explanation": "", "learningObjectives": ["081.01.01.01.15"], + "explanation": "", "variants": { "UbB45Q4p": { - "id": "UbB45Q4p", "type": "simple", + "id": "UbB45Q4p", "question": "Given:\np = pressure\nrho = density\nT = absolute temperature\nThe relationship between pressure, density and absolute temperature of a given mass of air can be expressed as follows:", "options": [ { @@ -18796,12 +18796,12 @@ }, { "id": "QCV9RGKAJQ", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "ESme4FQ7": { - "id": "ESme4FQ7", "type": "simple", + "id": "ESme4FQ7", "question": "A positively cambered aerofoil will generate zero lift:", "options": [ { @@ -18837,12 +18837,12 @@ }, { "id": "QCYEAZ7TW8", - "explanation": "", "learningObjectives": ["081.01.01.05.10"], + "explanation": "", "variants": { "k1WpojTD": { - "id": "k1WpojTD", "type": "simple", + "id": "k1WpojTD", "question": "Upon extension of a wing spoiler, if the angle of attack remains constant", "options": [ { @@ -18878,12 +18878,12 @@ }, { "id": "QCZLGQUHXL", - "explanation": "", "learningObjectives": ["081.01.04.03.07"], + "explanation": "", "variants": { "kftK4jHX": { - "id": "kftK4jHX", "type": "simple", + "id": "kftK4jHX", "question": "What is the consequence of decreasing the wing's upwash?", "options": [ { @@ -18919,12 +18919,12 @@ }, { "id": "QD1BY46DD9", - "explanation": "", "learningObjectives": ["081.01.09.01.09"], + "explanation": "", "variants": { "1tVX9GXY": { - "id": "1tVX9GXY", "type": "simple", + "id": "1tVX9GXY", "question": "While performing the “After Engine Start” procedures, the pilots of a commercial jet aircraft forget to set the slats/flaps in the calculated take-off position. What could be a consequence of this action?", "options": [ { @@ -18960,12 +18960,12 @@ }, { "id": "QZOWIVEE61", - "explanation": "", "learningObjectives": ["081.01.01.01.11"], + "explanation": "", "variants": { "6NHtgopG": { - "id": "6NHtgopG", "type": "simple", + "id": "6NHtgopG", "question": "Which one of the following statements about Bernoulli's theorem is correct?", "options": [ { @@ -18998,8 +18998,8 @@ "explanation": "" }, "ntGsDFXH": { - "id": "ntGsDFXH", "type": "simple", + "id": "ntGsDFXH", "question": "Which one of the following statements about Bernoulli's theorem is correct?", "options": [ { @@ -19035,12 +19035,12 @@ }, { "id": "QD75SDIG2Z", - "explanation": "", "learningObjectives": ["081.01.06.01.01"], + "explanation": "", "variants": { "wzd7LaVQ": { - "id": "wzd7LaVQ", "type": "simple", + "id": "wzd7LaVQ", "question": "Which statement about an aeroplane leaving ground effect is correct?\n\n1. The downwash angle increases.\n\n2. The induced angle of attack remains constant.", "options": [ { @@ -19080,8 +19080,8 @@ "explanation": "" }, "vmFUsRcA": { - "id": "vmFUsRcA", "type": "simple", + "id": "vmFUsRcA", "question": "Which statement about an aeroplane entering ground effect is correct?\n\n1. The downwash angle remains constant.\n\n2. The induced angle of attack decreases.", "options": [ { @@ -19117,12 +19117,12 @@ }, { "id": "QDI04P17TN", - "explanation": "", "learningObjectives": ["081.01.03.03.01"], + "explanation": "", "variants": { "t8KSx6l5": { - "id": "t8KSx6l5", "type": "simple", + "id": "t8KSx6l5", "question": "What is the relationship between velocity and drag on a 2-dimensional diagram?", "options": [ { @@ -19158,12 +19158,12 @@ }, { "id": "QDL7JXQIM2", - "explanation": "", "learningObjectives": ["081.01.12.02.02"], + "explanation": "", "variants": { "dc2CiFRv": { - "id": "dc2CiFRv", "type": "simple", + "id": "dc2CiFRv", "question": "What effect does ageing of an aeroplane have on the boundary layer condition?", "options": [ { @@ -19199,12 +19199,12 @@ }, { "id": "QDLW44G95T", - "explanation": "", "learningObjectives": ["081.01.04.03.03"], + "explanation": "", "variants": { "LhUb8Rwy": { - "id": "LhUb8Rwy", "type": "simple", + "id": "LhUb8Rwy", "question": "Increasing induced drag will ....(1).... VMD in level flight and increasing Parasite Drag will ....(2).... VMD in level flight:", "options": [ { @@ -19240,12 +19240,12 @@ }, { "id": "QDLZ1VN2YB", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "raOGiuQb": { - "id": "raOGiuQb", "type": "simple", + "id": "raOGiuQb", "question": "The forces of lift and drag on an aerofoil are, respectively, normal and parallel to the...", "options": [ { @@ -19286,12 +19286,12 @@ }, { "id": "QDO0Q5MZ8J", - "explanation": "", "learningObjectives": ["081.01.01.01.01"], + "explanation": "", "variants": { "F4GTv9Dm": { - "id": "F4GTv9Dm", "type": "simple", + "id": "F4GTv9Dm", "question": "The SI units of air density and force are respectively..", "options": [ { @@ -19327,12 +19327,12 @@ }, { "id": "QDPIKR3D1K", - "explanation": "", "learningObjectives": ["081.01.04.03.04"], + "explanation": "", "variants": { "LfYA954M": { - "id": "LfYA954M", "type": "simple", + "id": "LfYA954M", "question": "What is the effect on induced drag of mass and speed changes?\n(Note: all other factors of importance remaining constant)", "options": [ { @@ -19368,12 +19368,12 @@ }, { "id": "QDSQ3POUBV", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "HygQ6pJy": { - "id": "HygQ6pJy", "type": "simple", + "id": "HygQ6pJy", "question": "Regarding a symmetrical aerofoil section, which statement is correct? When the Angle Of Attack", "options": [ { @@ -19409,12 +19409,12 @@ }, { "id": "QDUKF3OMJX", - "explanation": "", "learningObjectives": ["081.01.05.07.05"], + "explanation": "", "variants": { "7s8fQFLI": { - "id": "7s8fQFLI", "type": "simple", + "id": "7s8fQFLI", "question": "An aeroplane on final approach is flying at a CAS lower than V~MD~, which means it is speed unstable. If the speed suddenly decreases, what effect do parasite and induced drag have on total drag?", "options": [ { @@ -19450,12 +19450,12 @@ }, { "id": "QDV18PHAB1", - "explanation": "", "learningObjectives": ["081.01.04.03.02"], + "explanation": "", "variants": { "m2j7xSHB": { - "id": "m2j7xSHB", "type": "simple", + "id": "m2j7xSHB", "question": "Calculate the new value of drag force, given: An airplane flying at 100 kt at an angle (alpha 1) of 4º, has a drag coefficient (CD1) of 0.028. Total drag force is 900 N. \n The airplane decelerates to 55 kt, flying at an angle of attack (alpha 2) of 15º, when drag coefficient (CD~2~) is 0.148.", "options": [ { @@ -19491,12 +19491,12 @@ }, { "id": "QDX4YM46IF", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "vJV6stMa": { - "id": "vJV6stMa", "type": "simple", + "id": "vJV6stMa", "question": "Regarding a symmetrical aerofoil section, which statement is correct? The Lift Coefficient..", "options": [ { @@ -19532,12 +19532,12 @@ }, { "id": "QDYZLU3DDA", - "explanation": "", "learningObjectives": ["081.01.02.01.02"], + "explanation": "", "variants": { "B38OCmPN": { - "id": "B38OCmPN", "type": "simple", + "id": "B38OCmPN", "question": "Which of these statements about a steady subsonic flow are correct or incorrect?\n\n1. The static pressure decreases as the streamlines diverge.2. The velocity does not change as the streamlines diverge.", "options": [ { @@ -19577,8 +19577,8 @@ "explanation": "" }, "VSJNsXpb": { - "id": "VSJNsXpb", "type": "simple", + "id": "VSJNsXpb", "question": "Which of these statements about a steady subsonic flow are correct or incorrect?\n\n1. The static pressure does not change as the streamlines diverge.2. The velocity decreases as the streamlines diverge.", "options": [ { @@ -19611,8 +19611,8 @@ "explanation": "" }, "BvKo4uFs": { - "id": "BvKo4uFs", "type": "simple", + "id": "BvKo4uFs", "question": "Which of these statements about a steady subsonic flow are correct or incorrect?\n\n1. The static pressure increases as the streamlines diverge.2. The velocity does not change as the streamlines diverge.", "options": [ { @@ -19645,8 +19645,8 @@ "explanation": "" }, "lIeTvASf": { - "id": "lIeTvASf", "type": "simple", + "id": "lIeTvASf", "question": "Which of these statements about a steady subsonic flow are correct or incorrect?\n\n1. The static pressure does not change as the streamlines diverge.2. The velocity increases as the streamlines diverge.", "options": [ { @@ -19682,12 +19682,12 @@ }, { "id": "QX9AWOYEZ7", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "aWTjw2zB": { - "id": "aWTjw2zB", "type": "simple", + "id": "aWTjw2zB", "question": "Select the correct statement with regard to positively cambered aerofoils.", "options": [ { @@ -19720,8 +19720,8 @@ "explanation": "" }, "tQVeJMAQ": { - "id": "tQVeJMAQ", "type": "simple", + "id": "tQVeJMAQ", "question": "Select the correct statement with regard to positively cambered aerofoils.", "options": [ { @@ -19757,12 +19757,12 @@ }, { "id": "QE4RVQXT4M", - "explanation": "", "learningObjectives": ["081.01.09.01.05"], + "explanation": "", "variants": { "dIUxnn38": { - "id": "dIUxnn38", "type": "simple", + "id": "dIUxnn38", "question": "Under what configuration is the aircraft at maximum C~L~/C~D~ ratio?", "options": [ { @@ -19798,12 +19798,12 @@ }, { "id": "QE5R6CHOXA", - "explanation": "", "learningObjectives": ["081.01.09.01.01"], + "explanation": "", "variants": { "8AulwVl3": { - "id": "8AulwVl3", "type": "simple", + "id": "8AulwVl3", "question": "Refer to figure 081-38.\nWhich of the following devices shows a slotted flap system?", "options": [ { @@ -19842,12 +19842,12 @@ }, { "id": "QE642TFRKS", - "explanation": "", "learningObjectives": ["081.01.01.03.08"], + "explanation": "", "variants": { "7vc6XODC": { - "id": "7vc6XODC", "type": "simple", + "id": "7vc6XODC", "question": "The angle of attack is the angle between:", "options": [ { @@ -19883,12 +19883,12 @@ }, { "id": "QJUV88ZVWP", - "explanation": "", "learningObjectives": ["081.01.01.04.03"], + "explanation": "", "variants": { "rwyYLZdf": { - "id": "rwyYLZdf", "type": "simple", + "id": "rwyYLZdf", "question": "The chord line of an aerofoil section is:", "options": [ { @@ -19924,12 +19924,12 @@ }, { "id": "QE97ZWOWUI", - "explanation": "", "learningObjectives": ["081.01.01.01.16"], + "explanation": "", "variants": { "XfO3Bmsq": { - "id": "XfO3Bmsq", "type": "simple", + "id": "XfO3Bmsq", "question": "The equation of continuity takes in account:", "options": [ { @@ -19965,12 +19965,12 @@ }, { "id": "QEAC0TQNP2", - "explanation": "", "learningObjectives": ["081.01.05.07.05"], + "explanation": "", "variants": { "g6PipRr0": { - "id": "g6PipRr0", "type": "simple", + "id": "g6PipRr0", "question": "An aeroplane is on final approach at a CAS within the non-stable region of the CAS/drag graph. The aeroplane experiences a change in the wind direction to be less of a headwind with little change in wind speed. This condition will cause...", "options": [ { @@ -20006,12 +20006,12 @@ }, { "id": "QSR0DE0PSV", - "explanation": "", "learningObjectives": ["081.01.01.05.10"], + "explanation": "", "variants": { "eE9OI50x": { - "id": "eE9OI50x", "type": "simple", + "id": "eE9OI50x", "question": "Wing sweep angle is the angle between:", "options": [ { @@ -20053,12 +20053,12 @@ }, { "id": "QEAWR0UBIR", - "explanation": "", "learningObjectives": ["081.01.01.01.11"], + "explanation": "", "variants": { "ytDqiUSK": { - "id": "ytDqiUSK", "type": "simple", + "id": "ytDqiUSK", "question": "Bernoulli's theorem states that in a perfect and constant airstream:", "options": [ { @@ -20094,12 +20094,12 @@ }, { "id": "QEEO5RDG77", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "Pz6vS7Wy": { - "id": "Pz6vS7Wy", "type": "simple", + "id": "Pz6vS7Wy", "question": "Where is the Centre of Pressure (CP) in relation to the Aerodynamic Centre (AC) on a positively cambered aerofoil?", "options": [ { @@ -20135,12 +20135,12 @@ }, { "id": "QEHVQPHS0D", - "explanation": "", "learningObjectives": ["081.01.02.06.02"], + "explanation": "", "variants": { "BnaPHEDp": { - "id": "BnaPHEDp", "type": "simple", + "id": "BnaPHEDp", "question": "An aircraft with dirt on the airframe is subject to what type of drag?", "options": [ { @@ -20176,12 +20176,12 @@ }, { "id": "QEIOQ30LG4", - "explanation": "", "learningObjectives": ["081.01.04.03.03"], + "explanation": "", "variants": { "B4fLBgyu": { - "id": "B4fLBgyu", "type": "simple", + "id": "B4fLBgyu", "question": "The value of the induced drag of an aeroplane in straight and level flight at constant mass varies linearly with", "options": [ { @@ -20217,12 +20217,12 @@ }, { "id": "QEJTHVA72Y", - "explanation": "", "learningObjectives": ["081.01.01.05.12"], + "explanation": "", "variants": { "kPkWw2sw": { - "id": "kPkWw2sw", "type": "simple", + "id": "kPkWw2sw", "question": "The angle between the aeroplane longitudinal axis and the wing root chord line is the", "options": [ { @@ -20258,12 +20258,12 @@ }, { "id": "QEK9Z9FMZD", - "explanation": "", "learningObjectives": ["081.01", "081.02"], + "explanation": "", "variants": { "JneCJIGX": { - "id": "JneCJIGX", "type": "simple", + "id": "JneCJIGX", "question": "Why are Vortex generators mounted on the upper wing surface?", "options": [ { @@ -20299,12 +20299,12 @@ }, { "id": "QEKP30RSNL", - "explanation": "", "learningObjectives": ["081.01.01.02.03"], + "explanation": "", "variants": { "KeXIQ2jk": { - "id": "KeXIQ2jk", "type": "simple", + "id": "KeXIQ2jk", "question": "Consider a steady, low subsonic flow through a stream tube. An increase in the temperature of the airflow will...", "options": [ { @@ -20340,12 +20340,12 @@ }, { "id": "QEODFLOCFY", - "explanation": "", "learningObjectives": ["081.01.04.03.06"], + "explanation": "", "variants": { "bShZCQdh": { - "id": "bShZCQdh", "type": "simple", + "id": "bShZCQdh", "question": "Which plane and situation experiences the most amount of lift reduction?", "options": [ { @@ -20381,12 +20381,12 @@ }, { "id": "QEQVQDW3W2", - "explanation": "", "learningObjectives": ["081.01.01.01.11"], + "explanation": "", "variants": { "69LEGy4P": { - "id": "69LEGy4P", "type": "simple", + "id": "69LEGy4P", "question": "In any given airflow, rho x A x V = constant, where:\n**rho = densityA = cross-sectional area of the flowV = Velocity**\nWhat is this principle known as?", "options": [ { @@ -20422,12 +20422,12 @@ }, { "id": "QEY67IJDAL", - "explanation": "", "learningObjectives": ["081.01.04.03.03"], + "explanation": "", "variants": { "qaGBlqzw": { - "id": "qaGBlqzw", "type": "simple", + "id": "qaGBlqzw", "question": "An aeroplane accelerates from 80 kt to 160 kt at a load factor equal to 1. By what factors will the induced drag coefficient (i) and the induced drag (ii) change?", "options": [ { @@ -20460,8 +20460,8 @@ "explanation": "" }, "KarZDGtn": { - "id": "KarZDGtn", "type": "simple", + "id": "KarZDGtn", "question": "An aeroplane accelerates from 80 kt to 160 kt at a load factor equal to 1 By what factors will the induced drag coefficient (i) and the induced drag (ii) change?", "options": [ { @@ -20497,12 +20497,12 @@ }, { "id": "QEYU7RUAD6", - "explanation": "", "learningObjectives": ["081.01.04.03.13"], + "explanation": "", "variants": { "Mmo6BGEd": { - "id": "Mmo6BGEd", "type": "simple", + "id": "Mmo6BGEd", "question": "Refer to image.\nIn the diagram an aircraft Polar diagram of CL against CD, point B is:", "options": [ { @@ -20538,12 +20538,12 @@ }, { "id": "QF0UENVN1Z", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "dgDyFlr2": { - "id": "dgDyFlr2", "type": "simple", + "id": "dgDyFlr2", "question": "Refer to figure. \n The trailing edge flaps are stuck in the position shown in the picture. What would the pilot have to do?", "options": [ { @@ -20579,12 +20579,12 @@ }, { "id": "QF5HN365QF", - "explanation": "", "learningObjectives": ["081.01.01.01.11"], + "explanation": "", "variants": { "mvgfnfyz": { - "id": "mvgfnfyz", "type": "simple", + "id": "mvgfnfyz", "question": "According to Bernoulli's theorem, which of the following is true?", "options": [ { @@ -20620,12 +20620,12 @@ }, { "id": "QFAG31I91V", - "explanation": "", "learningObjectives": ["081.01.10.02.03"], + "explanation": "", "variants": { "PTzszQga": { - "id": "PTzszQga", "type": "simple", + "id": "PTzszQga", "question": "As the speed of an aircraft at 20,000ft increases\nParasite Drag:", "options": [ { @@ -20661,12 +20661,12 @@ }, { "id": "QFBD6HZSWO", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "emLaK9hA": { - "id": "emLaK9hA", "type": "simple", + "id": "emLaK9hA", "question": "Coefficient of lift is", "options": [ { @@ -20702,12 +20702,12 @@ }, { "id": "QFBM1RKD59", - "explanation": "", "learningObjectives": ["081.01.09.02.02"], + "explanation": "", "variants": { "f0hCDle1": { - "id": "f0hCDle1", "type": "simple", + "id": "f0hCDle1", "question": "A slat will:", "options": [ { @@ -20743,12 +20743,12 @@ }, { "id": "QFE1O8OZP8", - "explanation": "", "learningObjectives": ["081.01.02.09.02"], + "explanation": "", "variants": { "sqXWsVJi": { - "id": "sqXWsVJi", "type": "simple", + "id": "sqXWsVJi", "question": "Refer to the image. \nThe point in the annex corresponding to CL for minimum horizontal flight speed is:", "options": [ { @@ -20784,12 +20784,12 @@ }, { "id": "QFGXTWQOI5", - "explanation": "", "learningObjectives": ["081.01.06.01.01"], + "explanation": "", "variants": { "gLkDZJvo": { - "id": "gLkDZJvo", "type": "simple", + "id": "gLkDZJvo", "question": "You are planning to take off on runway XX. Field elevation is 52 ft. Wing span 30 ft. At what height is the downwash least?", "options": [ { @@ -20825,12 +20825,12 @@ }, { "id": "QFJTLF9WJF", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "6q3sMCjc": { - "id": "6q3sMCjc", "type": "simple", + "id": "6q3sMCjc", "question": "In straight and level flight at a speed of 1.7 VS, the lift coefficient, expressed as a percentage of its maximum CLMAX, would be:", "options": [ { @@ -20863,8 +20863,8 @@ "explanation": "" }, "AsJ0b2SI": { - "id": "AsJ0b2SI", "type": "simple", + "id": "AsJ0b2SI", "question": "In straight and level flight at a speed of 1.3 VS, the lift coefficient, expressed as a percentage of its maximum CLMAX, would be:", "options": [ { @@ -20897,8 +20897,8 @@ "explanation": "" }, "U0UasVCH": { - "id": "U0UasVCH", "type": "simple", + "id": "U0UasVCH", "question": "In straight and level flight at a speed of 1.4 VS, the lift coefficient, expressed as a percentage of its maximum CLMAX, would be:", "options": [ { @@ -20931,8 +20931,8 @@ "explanation": "" }, "Yogb8ycN": { - "id": "Yogb8ycN", "type": "simple", + "id": "Yogb8ycN", "question": "In straight and level flight at a speed of 1.2 VS, the lift coefficient, expressed as a percentage of its maximum CLMAX, would be:", "options": [ { @@ -20968,12 +20968,12 @@ }, { "id": "QFJUMK3934", - "explanation": "", "learningObjectives": ["081.01", "081.06"], + "explanation": "", "variants": { "w4RPggaA": { - "id": "w4RPggaA", "type": "simple", + "id": "w4RPggaA", "question": "An aeroplane in straight and level flight at 200 kt is subjected to a sudden disturbance in speed. Assuming the angle of attack remains constant initially and the load factor reaches a value of 1.69:", "options": [ { @@ -21006,8 +21006,8 @@ "explanation": "" }, "SF5bzMWu": { - "id": "SF5bzMWu", "type": "simple", + "id": "SF5bzMWu", "question": "An aeroplane in straight and level flight at 200 kt is subjected to a sudden disturbance in speed. Assuming the angle of attack remains constant initially and the load factor reaches a value of 1.44:", "options": [ { @@ -21040,8 +21040,8 @@ "explanation": "" }, "nD4rPb5I": { - "id": "nD4rPb5I", "type": "simple", + "id": "nD4rPb5I", "question": "An aeroplane in straight and level flight at 200 kt is subjected to a sudden disturbance in speed. Assuming the angle of attack remains constant initially and the load factor reaches a value of 1.21:", "options": [ { @@ -21074,8 +21074,8 @@ "explanation": "" }, "fMHv8VVT": { - "id": "fMHv8VVT", "type": "simple", + "id": "fMHv8VVT", "question": "An aeroplane in straight and level flight at 300 kt is subjected to a sudden disturbance in speed. Assuming the angle of attack remains constant initially and the load factor reaches a value of 1.21:", "options": [ { @@ -21108,8 +21108,8 @@ "explanation": "" }, "jeQP8AC0": { - "id": "jeQP8AC0", "type": "simple", + "id": "jeQP8AC0", "question": "An aeroplane in straight and level flight at 300 kt is subjected to a sudden disturbance in speed. Assuming the angle of attack remains constant initially and the load factor reaches a value of 1.69:", "options": [ { @@ -21142,8 +21142,8 @@ "explanation": "" }, "EjUNsknc": { - "id": "EjUNsknc", "type": "simple", + "id": "EjUNsknc", "question": "An aeroplane in straight and level flight at 300 kt is subjected to a sudden disturbance in speed. Assuming the angle of attack remains constant initially and the load factor reaches a value of 1.44:", "options": [ { @@ -21176,8 +21176,8 @@ "explanation": "" }, "kr26A3Wf": { - "id": "kr26A3Wf", "type": "simple", + "id": "kr26A3Wf", "question": "An aeroplane in straight and level flight at 100 kt is subjected to a sudden disturbance in speed. Assuming the angle of attack remains constant initially and the load factor reaches a value of 1.21:", "options": [ { @@ -21210,8 +21210,8 @@ "explanation": "" }, "gczx7CJE": { - "id": "gczx7CJE", "type": "simple", + "id": "gczx7CJE", "question": "An aeroplane in straight and level flight at 100 kt is subjected to a sudden disturbance in speed. Assuming the angle of attack remains constant initially and the load factor reaches a value of 1.44:", "options": [ { @@ -21244,8 +21244,8 @@ "explanation": "" }, "tKEP7Bmn": { - "id": "tKEP7Bmn", "type": "simple", + "id": "tKEP7Bmn", "question": "An aeroplane in straight and level flight at 100 kt is subjected to a sudden disturbance in speed. Assuming the angle of attack remains constant initially and the load factor reaches a value of 1.96:", "options": [ { @@ -21278,8 +21278,8 @@ "explanation": "" }, "RjhwcrGa": { - "id": "RjhwcrGa", "type": "simple", + "id": "RjhwcrGa", "question": "An aeroplane in straight and level flight at 100 kt is subjected to a sudden disturbance in speed. Assuming the angle of attack remains constant initially and the load factor reaches a value of 1.69:", "options": [ { @@ -21312,8 +21312,8 @@ "explanation": "" }, "coOCwcsJ": { - "id": "coOCwcsJ", "type": "simple", + "id": "coOCwcsJ", "question": "An aeroplane in straight and level flight at 100 kt is subjected to a sudden disturbance in speed. Assuming the angle of attack remains constant initially and the load factor reaches a value of 2.25:", "options": [ { @@ -21346,8 +21346,8 @@ "explanation": "" }, "vMBe3AbH": { - "id": "vMBe3AbH", "type": "simple", + "id": "vMBe3AbH", "question": "An aeroplane in straight and level flight at 300 kt is subjected to a sudden disturbance in speed. Assuming the angle of attack remains constant initially and the load factor reaches a value of approximately 1.2:", "options": [ { @@ -21380,8 +21380,8 @@ "explanation": "" }, "Ml1BMVlQ": { - "id": "Ml1BMVlQ", "type": "simple", + "id": "Ml1BMVlQ", "question": "An aeroplane in straight and level flight at 300 kts is subjected to a sudden disturbance in speed. Assuming the angle of attack remains constant initially and the load factor reaches a value of approximately 1.2:", "options": [ { @@ -21417,12 +21417,12 @@ }, { "id": "QPPDIFQS1N", - "explanation": "", "learningObjectives": ["081.01.04.03.15"], + "explanation": "", "variants": { "7kTxTLGr": { - "id": "7kTxTLGr", "type": "simple", + "id": "7kTxTLGr", "question": "The highest value of the CL/CD ratio of an aeroplane is obtained:", "options": [ { @@ -21458,12 +21458,12 @@ }, { "id": "QFPGP0VS5T", - "explanation": "", "learningObjectives": ["081.01.09.03.01"], + "explanation": "", "variants": { "dv76KxSH": { - "id": "dv76KxSH", "type": "simple", + "id": "dv76KxSH", "question": "Vortex generators", "options": [ { @@ -21504,12 +21504,12 @@ }, { "id": "QFRCBV5800", - "explanation": "", "learningObjectives": ["081.01.04.02.07"], + "explanation": "", "variants": { "x4mKvRA6": { - "id": "x4mKvRA6", "type": "simple", + "id": "x4mKvRA6", "question": "With flaps deployed, at a constant IAS in straight and level flight, the magnitude of tip vortices:", "options": [ { @@ -21545,12 +21545,12 @@ }, { "id": "QG15TKIRL9", - "explanation": "", "learningObjectives": ["081.01.01.01.11"], + "explanation": "", "variants": { "Yal64aO1": { - "id": "Yal64aO1", "type": "simple", + "id": "Yal64aO1", "question": "Bernoulli's equation is:\n(note: rho is density; PSTAT is static pressure; PDYN is dynamic pressure; PTOT is total pressure)", "options": [ { @@ -21586,12 +21586,12 @@ }, { "id": "QG4DIALAUN", - "explanation": "", "learningObjectives": ["081.01.04.02.03"], + "explanation": "", "variants": { "XbtwYyKU": { - "id": "XbtwYyKU", "type": "simple", + "id": "XbtwYyKU", "question": "What would be the best way to reduce wing tip vortices?", "options": [ { @@ -21627,12 +21627,12 @@ }, { "id": "QG5G1CBOWE", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "FxW4rdbu": { - "id": "FxW4rdbu", "type": "simple", + "id": "FxW4rdbu", "question": "Which wing and tailplane constellation will have the least effect on the ground effect?", "options": [ { @@ -21668,12 +21668,12 @@ }, { "id": "QG5TEJK19A", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "4OcBOldD": { - "id": "4OcBOldD", "type": "simple", + "id": "4OcBOldD", "question": "What will happen if flaps are deployed further?", "options": [ { @@ -21709,12 +21709,12 @@ }, { "id": "QG6OPL4V7Y", - "explanation": "", "learningObjectives": ["081.01.05.02.03"], + "explanation": "", "variants": { "RLxIljIF": { - "id": "RLxIljIF", "type": "simple", + "id": "RLxIljIF", "question": "Interference drag is the result of", "options": [ { @@ -21755,12 +21755,12 @@ }, { "id": "QG6X1NRGH0", - "explanation": "", "learningObjectives": ["081.01.01.01.01"], + "explanation": "", "variants": { "8OoOPghB": { - "id": "8OoOPghB", "type": "simple", + "id": "8OoOPghB", "question": "What is the unit of measurement for power?", "options": [ { @@ -21793,8 +21793,8 @@ "explanation": "" }, "FOKPLsL9": { - "id": "FOKPLsL9", "type": "simple", + "id": "FOKPLsL9", "question": "What is the unit of measurement for power?", "options": [ { @@ -21830,12 +21830,12 @@ }, { "id": "QGA5VDKMH1", - "explanation": "", "learningObjectives": ["081.01.03.03.02"], + "explanation": "", "variants": { "ivTaiJ2b": { - "id": "ivTaiJ2b", "type": "simple", + "id": "ivTaiJ2b", "question": "Refer to figure. \n Assuming all bodies have the same cross-sectional area and are in motion, which body will have the highest form drag?", "options": [ { @@ -21871,12 +21871,12 @@ }, { "id": "QGAS0J15RU", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "Hc3XQ8Qj": { - "id": "Hc3XQ8Qj", "type": "simple", + "id": "Hc3XQ8Qj", "question": "Which aircraft design would be the most sensitive to changes in airflow patterns when entering ground effect?", "options": [ { @@ -21912,12 +21912,12 @@ }, { "id": "QGCU5TUFCW", - "explanation": "", "learningObjectives": ["081.01.04.03.03"], + "explanation": "", "variants": { "Mq3UQp6v": { - "id": "Mq3UQp6v", "type": "simple", + "id": "Mq3UQp6v", "question": "When entering a level turn at constant speed induced drag:", "options": [ { @@ -21953,12 +21953,12 @@ }, { "id": "QGDOWR2I0J", - "explanation": "", "learningObjectives": ["081.01.04.03.06"], + "explanation": "", "variants": { "wa2NAOdd": { - "id": "wa2NAOdd", "type": "simple", + "id": "wa2NAOdd", "question": "When wing lift is zero, its induced drag is:", "options": [ { @@ -21994,12 +21994,12 @@ }, { "id": "QGJPYTVPW3", - "explanation": "", "learningObjectives": ["081.01.02.07.01"], + "explanation": "", "variants": { "MqyYl2LY": { - "id": "MqyYl2LY", "type": "simple", + "id": "MqyYl2LY", "question": "Lift acts through:", "options": [ { @@ -22035,12 +22035,12 @@ }, { "id": "QGOI8U6GR5", - "explanation": "", "learningObjectives": ["081.01.01.05.11"], + "explanation": "", "variants": { "VYllieMd": { - "id": "VYllieMd", "type": "simple", + "id": "VYllieMd", "question": "The purpose of wing twist is to:", "options": [ { @@ -22076,12 +22076,12 @@ }, { "id": "QGUTYLUHQ6", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "4Tu8eCd4": { - "id": "4Tu8eCd4", "type": "simple", + "id": "4Tu8eCd4", "question": "The lift coefficient of a symmetrical aerofoil section at zero angle of attack is:", "options": [ { @@ -22114,8 +22114,8 @@ "explanation": "" }, "yHW69NE6": { - "id": "yHW69NE6", "type": "simple", + "id": "yHW69NE6", "question": "The lift coefficient of a symmetrical aerofoil section at zero angle of attack is:", "options": [ { @@ -22148,8 +22148,8 @@ "explanation": "" }, "SyaTQcQG": { - "id": "SyaTQcQG", "type": "simple", + "id": "SyaTQcQG", "question": "The lift coefficient of a symmetrical aerofoil section at zero angle of attack is:", "options": [ { @@ -22182,8 +22182,8 @@ "explanation": "" }, "dQooFnHE": { - "id": "dQooFnHE", "type": "simple", + "id": "dQooFnHE", "question": "The lift coefficient of a symmetrical aerofoil section at zero angle of attack is:", "options": [ { @@ -22219,12 +22219,12 @@ }, { "id": "QH1F9ETO63", - "explanation": "", "learningObjectives": ["081.01.01.03.08"], + "explanation": "", "variants": { "B5jhlNrR": { - "id": "B5jhlNrR", "type": "simple", + "id": "B5jhlNrR", "question": "The angle of attack, alpha, is the angle between:", "options": [ { @@ -22260,12 +22260,12 @@ }, { "id": "QH3OYEQBZN", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "eO7HnQ1d": { - "id": "eO7HnQ1d", "type": "simple", + "id": "eO7HnQ1d", "question": "An aeroplane with swept back wings is equipped with slats and/or leading edge (LE) flaps. One possible efficient way to arrange the leading edge devices on the wings is?", "options": [ { @@ -22301,12 +22301,12 @@ }, { "id": "QH55B2T42O", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "F2WXp0wM": { - "id": "F2WXp0wM", "type": "simple", + "id": "F2WXp0wM", "question": "When the lift coefficient of a positively cambered aerofoil section is zero, the pitching moment is..", "options": [ { @@ -22339,8 +22339,8 @@ "explanation": "" }, "q4rVJUU9": { - "id": "q4rVJUU9", "type": "simple", + "id": "q4rVJUU9", "question": "When the lift coefficient of a negatively cambered aerofoil section is zero, the pitching moment is..", "options": [ { @@ -22376,12 +22376,12 @@ }, { "id": "QH5T6QHJZM", - "explanation": "", "learningObjectives": ["081.01.01.04.03"], + "explanation": "", "variants": { "ewFJxtDJ": { - "id": "ewFJxtDJ", "type": "simple", + "id": "ewFJxtDJ", "question": "Refer to figure. The correct sequence that represents the ordering of the aerofoils by increasing C~L~ is:", "options": [ { @@ -22417,12 +22417,12 @@ }, { "id": "QH89886BHT", - "explanation": "", "learningObjectives": ["081.01.01.03.08"], + "explanation": "", "variants": { "eZVyIrhF": { - "id": "eZVyIrhF", "type": "simple", + "id": "eZVyIrhF", "question": "The induced angle of attack is the result of:", "options": [ { @@ -22460,8 +22460,8 @@ "explanation": "" }, "eRd9ZKnl": { - "id": "eRd9ZKnl", "type": "simple", + "id": "eRd9ZKnl", "question": "The induced angle of attack is the result of:", "options": [ { @@ -22497,12 +22497,12 @@ }, { "id": "QHE34CVI8U", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "Ig9GJQ9R": { - "id": "Ig9GJQ9R", "type": "simple", + "id": "Ig9GJQ9R", "question": "Compared to a clean aerofoil, an aerofoil which has dirt and other particles increases what type of drag?", "options": [ { @@ -22535,8 +22535,8 @@ "explanation": "" }, "SXddZi9G": { - "id": "SXddZi9G", "type": "simple", + "id": "SXddZi9G", "question": "Compared to a cleaned aerofoil, an aerofoil which has dirt and other particles increases what type of drag?", "options": [ { @@ -22572,12 +22572,12 @@ }, { "id": "QHE5ZCMYJW", - "explanation": "", "learningObjectives": ["081.01.09.03.01"], + "explanation": "", "variants": { "3Rvu2nrs": { - "id": "3Rvu2nrs", "type": "simple", + "id": "3Rvu2nrs", "question": "The purpose of vortex generators is:", "options": [ { @@ -22613,12 +22613,12 @@ }, { "id": "QHIC6QLWMV", - "explanation": "", "learningObjectives": ["081.01.02.07.01"], + "explanation": "", "variants": { "SzSXIfim": { - "id": "SzSXIfim", "type": "simple", + "id": "SzSXIfim", "question": "Alpha for best lift/drag ratio will be achieved\nat:", "options": [ { @@ -22654,12 +22654,12 @@ }, { "id": "QHJPQT4C1M", - "explanation": "", "learningObjectives": ["081.01.01.02.03"], + "explanation": "", "variants": { "rdl5mVMt": { - "id": "rdl5mVMt", "type": "simple", + "id": "rdl5mVMt", "question": "Consider a subsonic airflow moving steadily through the Venturi Tube with no leaks, as represented in the image.\n\"a, b, c, d\" identify areas of different speeds. The sequence that represents an increasing magnitude of airflow speed is:", "options": [ { @@ -22695,12 +22695,12 @@ }, { "id": "QHMNSZPFPS", - "explanation": "", "learningObjectives": ["081.01.09.01.08"], + "explanation": "", "variants": { "bAw2wUX3": { - "id": "bAw2wUX3", "type": "simple", + "id": "bAw2wUX3", "question": "How will the takeoff distance change if the flaps are increased from 0 to full?", "options": [ { @@ -22736,12 +22736,12 @@ }, { "id": "QHON61FYZK", - "explanation": "", "learningObjectives": ["081.01.01.01.11"], + "explanation": "", "variants": { "OY9yXNTO": { - "id": "OY9yXNTO", "type": "simple", + "id": "OY9yXNTO", "question": "Bernoulli's theorem states that", "options": [ { @@ -22777,12 +22777,12 @@ }, { "id": "QHPBMFLE25", - "explanation": "", "learningObjectives": ["081.01.03.02.01"], + "explanation": "", "variants": { "9s3wNp6H": { - "id": "9s3wNp6H", "type": "simple", + "id": "9s3wNp6H", "question": "The lift formula can be written as (rho = density)", "options": [ { @@ -22818,12 +22818,12 @@ }, { "id": "QHQ35X4A7U", - "explanation": "", "learningObjectives": ["081.01.01.01.07"], + "explanation": "", "variants": { "Y5T3y3cD": { - "id": "Y5T3y3cD", "type": "simple", + "id": "Y5T3y3cD", "question": "Static pressure acts:", "options": [ { @@ -22856,8 +22856,8 @@ "explanation": "" }, "mVi19gDQ": { - "id": "mVi19gDQ", "type": "simple", + "id": "mVi19gDQ", "question": "Static pressure acts:", "options": [ { @@ -22893,12 +22893,12 @@ }, { "id": "QHR7J2BW8D", - "explanation": "", "learningObjectives": ["081.01.06.01.01"], + "explanation": "", "variants": { "1xAHmwWL": { - "id": "1xAHmwWL", "type": "simple", + "id": "1xAHmwWL", "question": "Taking of from a Runway. Field elevation is 52 ft and your wing span is 30 ft. At what height is the downwash least?", "options": [ { @@ -22934,12 +22934,12 @@ }, { "id": "QHRT2ABX08", - "explanation": "", "learningObjectives": ["081.01.03.03.02"], + "explanation": "", "variants": { "HUtyMFOy": { - "id": "HUtyMFOy", "type": "simple", + "id": "HUtyMFOy", "question": "The frontal area of a body, placed in a certain airstream is increased by a factor 3. If the shape does not alter, the form drag will increase by a factor of", "options": [ { @@ -22972,8 +22972,8 @@ "explanation": "" }, "Ugpe204i": { - "id": "Ugpe204i", "type": "simple", + "id": "Ugpe204i", "question": "The frontal area of a body, placed in a certain airstream is increased by a factor 3 \n\nIf the shape does not alter, the form drag will increase by a factor of", "options": [ { @@ -23006,8 +23006,8 @@ "explanation": "" }, "uUg7lEKv": { - "id": "uUg7lEKv", "type": "simple", + "id": "uUg7lEKv", "question": "The frontal area of a body, placed in a certain airstream is increased by a factor 3. If the shape does not alter, the form drag will increase by a factor of:", "options": [ { @@ -23040,8 +23040,8 @@ "explanation": "" }, "vXMNYhMb": { - "id": "vXMNYhMb", "type": "simple", + "id": "vXMNYhMb", "question": "The frontal area of a body, placed in a certain airstream is increased by a factor 3. If the shape does not alter, the form drag will increase by a factor of:", "options": [ { @@ -23074,8 +23074,8 @@ "explanation": "" }, "qWqLVZEp": { - "id": "qWqLVZEp", "type": "simple", + "id": "qWqLVZEp", "question": "The frontal area of a body, placed in a certain airstream is increased by a factor 3. If the shape does not alter, the form drag will increase by a factor of:", "options": [ { @@ -23111,12 +23111,12 @@ }, { "id": "QHUVCOK68H", - "explanation": "", "learningObjectives": ["081.01.03.02.01"], + "explanation": "", "variants": { "umxDyxMg": { - "id": "umxDyxMg", "type": "simple", + "id": "umxDyxMg", "question": "The lift formula can be written as: (rho = density)", "options": [ { @@ -23149,8 +23149,8 @@ "explanation": "" }, "RdQamtmr": { - "id": "RdQamtmr", "type": "simple", + "id": "RdQamtmr", "question": "The lift formula can be written as: (rho = density)", "options": [ { @@ -23186,12 +23186,12 @@ }, { "id": "QHZRH0TQ3S", - "explanation": "", "learningObjectives": ["081.01.09.01.09"], + "explanation": "", "variants": { "xGsypRbe": { - "id": "xGsypRbe", "type": "simple", + "id": "xGsypRbe", "question": "After taking off from a runway and during climb, the pilot forgets to retract the flaps. What are the consequences?", "options": [ { @@ -23227,12 +23227,12 @@ }, { "id": "QHZVU1P0M9", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "NXPxAxCq": { - "id": "NXPxAxCq", "type": "simple", + "id": "NXPxAxCq", "question": "Regarding a symmetrical aerofoil section, which statement is correct? When the Lift Coefficient equals zero..", "options": [ { @@ -23268,12 +23268,12 @@ }, { "id": "QI03GW734I", - "explanation": "", "learningObjectives": ["081.01.12.02.01"], + "explanation": "", "variants": { "jN9evT7a": { - "id": "jN9evT7a", "type": "simple", + "id": "jN9evT7a", "question": "Drag with greatest influence due to an ageing airframe is identified as?", "options": [ { @@ -23309,12 +23309,12 @@ }, { "id": "QI0BFFZ8DQ", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "Z6vqkYKP": { - "id": "Z6vqkYKP", "type": "simple", + "id": "Z6vqkYKP", "question": "An aeroplane is in level flight, and has a coefficient of lift 0.6 and a coefficient of induced drag 0.1. The aircraft slows down while maintaining level flight. In order to maintain lift at the lower speed, the lift coefficient increases by a factor of 1.5. What is the new coefficient of induced drag if there is NO change in configuration?", "options": [ { @@ -23350,12 +23350,12 @@ }, { "id": "QLCT39OBB3", - "explanation": "", "learningObjectives": ["081.01.01.04.09"], + "explanation": "", "variants": { "N1ioJfJG": { - "id": "N1ioJfJG", "type": "simple", + "id": "N1ioJfJG", "question": "Select the correct statement in regard to a symmetrical aerofoil section.", "options": [ { @@ -23391,12 +23391,12 @@ }, { "id": "QVWQT8JBHK", - "explanation": "", "learningObjectives": ["081.01.01.02.01"], + "explanation": "", "variants": { "2hEdOQWJ": { - "id": "2hEdOQWJ", "type": "simple", + "id": "2hEdOQWJ", "question": "For a steady subsonic airflow, which statement is correct?", "options": [ { @@ -23432,12 +23432,12 @@ }, { "id": "QI1ZBH7D2T", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "kFGluug5": { - "id": "kFGluug5", "type": "simple", + "id": "kFGluug5", "question": "Refer to figure 081-38.\nArrange the flaps in order of increasing L/D ratio:", "options": [ { @@ -23476,12 +23476,12 @@ }, { "id": "QI3Y7SQU45", - "explanation": "", "learningObjectives": ["081.01.03.03.01"], + "explanation": "", "variants": { "cZWtP6Fv": { - "id": "cZWtP6Fv", "type": "simple", + "id": "cZWtP6Fv", "question": "Based on the two-dimensional drag formula, if the altitude increases while all other parameters remain constant, the drag will (1)___ because the air density will (2)___.", "options": [ { @@ -23517,12 +23517,12 @@ }, { "id": "QI4S361TNQ", - "explanation": "", "learningObjectives": ["081.01.01.01.04"], + "explanation": "", "variants": { "k4kaiqJq": { - "id": "k4kaiqJq", "type": "simple", + "id": "k4kaiqJq", "question": "Air with water vapour is:", "options": [ { @@ -23558,12 +23558,12 @@ }, { "id": "QI5B28I7G8", - "explanation": "", "learningObjectives": ["081.01.02.03.01"], + "explanation": "", "variants": { "SWDdWOPY": { - "id": "SWDdWOPY", "type": "simple", + "id": "SWDdWOPY", "question": "At a constant airspeed, a reduction in an aerofoil’s angle of attack results in the speed of the flow over the upper surface to..", "options": [ { @@ -23596,8 +23596,8 @@ "explanation": "" }, "6O1iBHrR": { - "id": "6O1iBHrR", "type": "simple", + "id": "6O1iBHrR", "question": "At a constant airspeed, a reduction in an aerofoil’s angle of attack results in the speed of the flow over the upper surface to...", "options": [ { @@ -23633,12 +23633,12 @@ }, { "id": "QI87IHJGQE", - "explanation": "", "learningObjectives": ["081.01.07.02.01"], + "explanation": "", "variants": { "lT78iQAf": { - "id": "lT78iQAf", "type": "simple", + "id": "lT78iQAf", "question": "If C~L~ has a value of 1.22 at a speed of 1.1 V~S~ , what is its value at a speed of 1.8 V~S~ ?", "options": [ { @@ -23674,12 +23674,12 @@ }, { "id": "QIDE8KLJNK", - "explanation": "", "learningObjectives": ["081.01.01.05.04"], + "explanation": "", "variants": { "bgfRjASC": { - "id": "bgfRjASC", "type": "simple", + "id": "bgfRjASC", "question": "The units of wing loading (I) W / S and (II) dynamic pressure q are:", "options": [ { @@ -23712,8 +23712,8 @@ "explanation": "" }, "MyHeXC5C": { - "id": "MyHeXC5C", "type": "simple", + "id": "MyHeXC5C", "question": "The units of wing loading (I) W / S and (II) dynamic pressure q are:", "options": [ { @@ -23749,12 +23749,12 @@ }, { "id": "QZBLTN7617", - "explanation": "", "learningObjectives": ["081.01.01.01.02"], + "explanation": "", "variants": { "xOGcgWWO": { - "id": "xOGcgWWO", "type": "simple", + "id": "xOGcgWWO", "question": "Which of these statements about weight or mass is correct?", "options": [ { @@ -23792,8 +23792,8 @@ "explanation": "" }, "2ID8Hjh1": { - "id": "2ID8Hjh1", "type": "simple", + "id": "2ID8Hjh1", "question": "Which of these statements about weight or mass is correct?", "options": [ { @@ -23826,8 +23826,8 @@ "explanation": "" }, "ZQhctvu3": { - "id": "ZQhctvu3", "type": "simple", + "id": "ZQhctvu3", "question": "Which of these statements about weight or mass is correct?", "options": [ { @@ -23860,8 +23860,8 @@ "explanation": "" }, "DHEnkPk7": { - "id": "DHEnkPk7", "type": "simple", + "id": "DHEnkPk7", "question": "Which of these statements about weight or mass is correct?", "options": [ { @@ -23899,8 +23899,8 @@ "explanation": "" }, "LtTlYcCk": { - "id": "LtTlYcCk", "type": "simple", + "id": "LtTlYcCk", "question": "Which of these statements about weight or mass is correct?", "options": [ { @@ -23933,8 +23933,8 @@ "explanation": "" }, "dxrs0Ctt": { - "id": "dxrs0Ctt", "type": "simple", + "id": "dxrs0Ctt", "question": "Which of these statements about weight or mass is correct?", "options": [ { @@ -23967,8 +23967,8 @@ "explanation": "" }, "8fZ2gSsx": { - "id": "8fZ2gSsx", "type": "simple", + "id": "8fZ2gSsx", "question": "Which of these statements about weight or mass is correct?", "options": [ { @@ -24001,8 +24001,8 @@ "explanation": "" }, "qG7ZVrUk": { - "id": "qG7ZVrUk", "type": "simple", + "id": "qG7ZVrUk", "question": "Which of these statements about weight or mass is correct?", "options": [ { @@ -24035,8 +24035,8 @@ "explanation": "" }, "vuhFI8L4": { - "id": "vuhFI8L4", "type": "simple", + "id": "vuhFI8L4", "question": "Which of these statements about weight or mass is correct?", "options": [ { @@ -24069,8 +24069,8 @@ "explanation": "" }, "bjXepaIV": { - "id": "bjXepaIV", "type": "simple", + "id": "bjXepaIV", "question": "Which of these statements about weight or mass is correct?", "options": [ { @@ -24103,8 +24103,8 @@ "explanation": "" }, "g2O5EaCu": { - "id": "g2O5EaCu", "type": "simple", + "id": "g2O5EaCu", "question": "Which of these statements about weight or mass is correct?", "options": [ { @@ -24137,8 +24137,8 @@ "explanation": "" }, "muuwMnxF": { - "id": "muuwMnxF", "type": "simple", + "id": "muuwMnxF", "question": "Which of these statements about weight or mass is correct?", "options": [ { @@ -24171,8 +24171,8 @@ "explanation": "" }, "0DA37hFC": { - "id": "0DA37hFC", "type": "simple", + "id": "0DA37hFC", "question": "Which of these statements about weight or mass is correct?", "options": [ { @@ -24205,8 +24205,8 @@ "explanation": "" }, "yDeWNSzF": { - "id": "yDeWNSzF", "type": "simple", + "id": "yDeWNSzF", "question": "Which of these statements about weight or mass is correct?", "options": [ { @@ -24239,8 +24239,8 @@ "explanation": "" }, "QpgYdE5L": { - "id": "QpgYdE5L", "type": "simple", + "id": "QpgYdE5L", "question": "Which of these statements about weight or mass is correct?", "options": [ { @@ -24276,12 +24276,12 @@ }, { "id": "QIFTZJCDDU", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "52IeC8aR": { - "id": "52IeC8aR", "type": "simple", + "id": "52IeC8aR", "question": "Given the following aeroplane configurations:\n\n1. Clean wing.2. Slats only extended.3. Flaps only extended.\nPlace these configurations in order of increasing critical angle of attack:\n ", "options": [ { @@ -24317,12 +24317,12 @@ }, { "id": "QIJTV3A8CA", - "explanation": "", "learningObjectives": ["081.01.09.01.06"], + "explanation": "", "variants": { "C5db35Q8": { - "id": "C5db35Q8", "type": "simple", + "id": "C5db35Q8", "question": "Deployment of trailing edge flaps will reduce the angle of attack at which CLmax is reached. The design of flap used to minimise this effect is: ", "options": [ { @@ -24358,12 +24358,12 @@ }, { "id": "QIO8WPZAI8", - "explanation": "", "learningObjectives": ["081.01.01.01.01"], + "explanation": "", "variants": { "KXGEfbAE": { - "id": "KXGEfbAE", "type": "simple", + "id": "KXGEfbAE", "question": "The following unit of measurement: kg·m/s^2^ is expressed in the SI-unit system as:", "options": [ { @@ -24399,12 +24399,12 @@ }, { "id": "QIONLMOMBY", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "WLFACxdB": { - "id": "WLFACxdB", "type": "simple", + "id": "WLFACxdB", "question": "A plane is flying at 1.8 V~S~, what percentage of C~Lmax~ is that?", "options": [ { @@ -24440,12 +24440,12 @@ }, { "id": "QIPU3IG51G", - "explanation": "", "learningObjectives": ["081.01.09.02.02"], + "explanation": "", "variants": { "o3AcEFBO": { - "id": "o3AcEFBO", "type": "simple", + "id": "o3AcEFBO", "question": "Slats:", "options": [ { @@ -24481,12 +24481,12 @@ }, { "id": "QIRY2HHT2Z", - "explanation": "", "learningObjectives": ["081.01.09.01.06"], + "explanation": "", "variants": { "74vcUcIv": { - "id": "74vcUcIv", "type": "simple", + "id": "74vcUcIv", "question": "When extending the trailing edge flaps the effective angle of attack:", "options": [ { @@ -24522,12 +24522,12 @@ }, { "id": "QIUG37BS1A", - "explanation": "", "learningObjectives": ["081.01.12.01.03"], + "explanation": "", "variants": { "XZW4uwWx": { - "id": "XZW4uwWx", "type": "simple", + "id": "XZW4uwWx", "question": "An aeroplane without icing protection ventures into atmospheric conditions where icing will occur. What effect will this have on the aeroplane?", "options": [ { @@ -24563,12 +24563,12 @@ }, { "id": "QJ0OCQ49FG", - "explanation": "", "learningObjectives": ["081.01.05.05.01"], + "explanation": "", "variants": { "VgDsJozc": { - "id": "VgDsJozc", "type": "simple", + "id": "VgDsJozc", "question": "Refer to figure 081-06.\nWhich line represents the total drag line of an aeroplane?", "options": [ { @@ -24607,12 +24607,12 @@ }, { "id": "QJ8L7VT145", - "explanation": "", "learningObjectives": ["081.01.01.05.03"], + "explanation": "", "variants": { "BBgY5P0n": { - "id": "BBgY5P0n", "type": "simple", + "id": "BBgY5P0n", "question": "Refer to figure. \n Given the wing planform represented in the diagram and the following dimensions: Span 12.5 m Root chord 1.5 m Tip chord 1.0 m.The correct values of wing area and taper ratio or aspect ratio are:", "options": [ { @@ -24648,12 +24648,12 @@ }, { "id": "QSZTY8B1OF", - "explanation": "", "learningObjectives": ["081.01.04.03.05"], + "explanation": "", "variants": { "VuadEHvu": { - "id": "VuadEHvu", "type": "simple", + "id": "VuadEHvu", "question": "In order to reduce friction drag, some wings are designed so that, compared to a conventional aerofoil...", "options": [ { @@ -24689,12 +24689,12 @@ }, { "id": "QJANXI8PXK", - "explanation": "", "learningObjectives": ["081.01.01.05.03"], + "explanation": "", "variants": { "X4RRvm3R": { - "id": "X4RRvm3R", "type": "simple", + "id": "X4RRvm3R", "question": "Aspect ratio of a tapered wing, is the ratio of", "options": [ { @@ -24730,12 +24730,12 @@ }, { "id": "QJCK6WEKPW", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "1ytHtnHD": { - "id": "1ytHtnHD", "type": "simple", + "id": "1ytHtnHD", "question": "An aerofoil with positive camber will produce:", "options": [ { @@ -24771,12 +24771,12 @@ }, { "id": "QJCM9H4RP1", - "explanation": "", "learningObjectives": ["081.01.01.05.03"], + "explanation": "", "variants": { "zpuB5az6": { - "id": "zpuB5az6", "type": "simple", + "id": "zpuB5az6", "question": "Taper ratio is...", "options": [ { @@ -24812,12 +24812,12 @@ }, { "id": "QJH31KHHB5", - "explanation": "", "learningObjectives": ["081.01.04.03.06"], + "explanation": "", "variants": { "YncWrG8d": { - "id": "YncWrG8d", "type": "simple", + "id": "YncWrG8d", "question": "Increased lift will increase the value of induced drag. Which of these types of drag will also increase?", "options": [ { @@ -24853,12 +24853,12 @@ }, { "id": "QJKOTUBVOI", - "explanation": "", "learningObjectives": ["081.01.10.01.03"], + "explanation": "", "variants": { "WxQFJVIE": { - "id": "WxQFJVIE", "type": "simple", + "id": "WxQFJVIE", "question": "The result of spoiler surfaces deploying are:", "options": [ { @@ -24894,12 +24894,12 @@ }, { "id": "QJLHCKHKRX", - "explanation": "", "learningObjectives": ["081.01.01.04.01"], + "explanation": "", "variants": { "NwhgWAhv": { - "id": "NwhgWAhv", "type": "simple", + "id": "NwhgWAhv", "question": "The centre of the pressure of a symmetrical aerofoil section is located at approximately ___ of the section chord behind the leading edge.", "options": [ { @@ -24935,12 +24935,12 @@ }, { "id": "QJLZ3SZ96T", - "explanation": "", "learningObjectives": ["081.01.02.02.01"], + "explanation": "", "variants": { "bqoeoXqm": { - "id": "bqoeoXqm", "type": "simple", + "id": "bqoeoXqm", "question": "Which characteristic describes the stagnation point at an aerofoil? The point where...", "options": [ { @@ -24976,12 +24976,12 @@ }, { "id": "QJVF1KPMV9", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "pFZkx72c": { - "id": "pFZkx72c", "type": "simple", + "id": "pFZkx72c", "question": "At a load factor of 1 and the aeroplane's minimum drag speed, what is the ratio between induced drag D~i~ and parasite drag D~p~?", "options": [ { @@ -25017,12 +25017,12 @@ }, { "id": "QJVYKBJJNX", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "AZHMzWaG": { - "id": "AZHMzWaG", "type": "simple", + "id": "AZHMzWaG", "question": "The forces acting on a symmetrical aerofoil element when the upstream airflow is parallel to the chord line:", "options": [ { @@ -25058,12 +25058,12 @@ }, { "id": "QJYG9DZDSR", - "explanation": "", "learningObjectives": ["081.01.06.01.02"], + "explanation": "", "variants": { "LJMJudVP": { - "id": "LJMJudVP", "type": "simple", + "id": "LJMJudVP", "question": "Which statement, about an aeroplane entering ground effect at constant angle of attack, is correct? \nI The lift coefficient CL decreases\nII The induced drag coefficient CDi increases.", "options": [ { @@ -25113,8 +25113,8 @@ "explanation": "" }, "MwmQeXJR": { - "id": "MwmQeXJR", "type": "simple", + "id": "MwmQeXJR", "question": "Which statement, about an aeroplane entering ground effect at constant angle of attack, is correct? \n\nI The lift coefficient CL increases\n II The induced drag coefficient CDi decreases.", "options": [ { @@ -25147,8 +25147,8 @@ "explanation": "" }, "0OgvXbHg": { - "id": "0OgvXbHg", "type": "simple", + "id": "0OgvXbHg", "question": "Which statement, about an aeroplane entering ground effect at constant angle of attack, is correct? \nI The lift coefficient CL increases\nII The induced drag coefficient CDi increases.", "options": [ { @@ -25181,8 +25181,8 @@ "explanation": "" }, "fVuyEDvO": { - "id": "fVuyEDvO", "type": "simple", + "id": "fVuyEDvO", "question": "Which statement, about an aeroplane entering ground effect at constant angle of attack, is correct? \n\nI The lift coefficient CL decreases\n II The induced drag coefficient CDi decreases.", "options": [ { @@ -25215,8 +25215,8 @@ "explanation": "" }, "Z93wjyeC": { - "id": "Z93wjyeC", "type": "simple", + "id": "Z93wjyeC", "question": "Which statement, about an aeroplane leaving ground effect at constant angle of attack, is correct? \nI The lift coefficient CL increases \nII The induced drag coefficient CDi increases.", "options": [ { @@ -25249,8 +25249,8 @@ "explanation": "" }, "fK3gwy23": { - "id": "fK3gwy23", "type": "simple", + "id": "fK3gwy23", "question": "Which statement, about an aeroplane leaving ground effect at constant angle of attack, is correct? \nI The lift coefficient CL increases\nII The induced drag coefficient CDi decreases.", "options": [ { @@ -25283,8 +25283,8 @@ "explanation": "" }, "xNB93qXR": { - "id": "xNB93qXR", "type": "simple", + "id": "xNB93qXR", "question": "Which statement, about an aeroplane leaving ground effect at constant angle of attack, is correct? \nI The lift coefficient CL decreases\nII The induced drag coefficient CDi decreases.", "options": [ { @@ -25317,8 +25317,8 @@ "explanation": "" }, "g3I0idcj": { - "id": "g3I0idcj", "type": "simple", + "id": "g3I0idcj", "question": "Which statement, about an aeroplane entering ground effect at constant angle of attack, is correct? \n\nI The lift coefficient CL remains constant\n II The induced drag coefficient CDi decreases.", "options": [ { @@ -25351,8 +25351,8 @@ "explanation": "" }, "l5LZ26Jo": { - "id": "l5LZ26Jo", "type": "simple", + "id": "l5LZ26Jo", "question": "Which statement, about an aeroplane entering ground effect at constant angle of attack, is correct? \n\nI The lift coefficient CL decreases\n II The induced drag coefficient CDi remains constant.", "options": [ { @@ -25385,8 +25385,8 @@ "explanation": "" }, "IU4hXSPH": { - "id": "IU4hXSPH", "type": "simple", + "id": "IU4hXSPH", "question": "Which statement, about an aeroplane entering ground effect at constant angle of attack, is correct? \n\nI The lift coefficient CL increases\n II The induced drag coefficient CDi remains constant.", "options": [ { @@ -25419,8 +25419,8 @@ "explanation": "" }, "flcFibHk": { - "id": "flcFibHk", "type": "simple", + "id": "flcFibHk", "question": "Which statement, about an aeroplane entering ground effect at constant angle of attack, is correct? \nI The lift coefficient CL remains constant\nII The induced drag coefficient CDi increases.", "options": [ { @@ -25453,8 +25453,8 @@ "explanation": "" }, "b35JzSc7": { - "id": "b35JzSc7", "type": "simple", + "id": "b35JzSc7", "question": "Which statement, about an aeroplane leaving ground effect at constant angle of attack, is correct? \nI The lift coefficient CL remains constant\nII The induced drag coefficient CDi increases.", "options": [ { @@ -25487,8 +25487,8 @@ "explanation": "" }, "WmdgyDES": { - "id": "WmdgyDES", "type": "simple", + "id": "WmdgyDES", "question": "Which statement, about an aeroplane leaving ground effect at constant angle of attack, is correct? \nI The lift coefficient CL increases\nII The induced drag coefficient CDi remains constant.", "options": [ { @@ -25521,8 +25521,8 @@ "explanation": "" }, "O8z4P89w": { - "id": "O8z4P89w", "type": "simple", + "id": "O8z4P89w", "question": "Which statement, about an aeroplane leaving ground effect at constant angle of attack, is correct? \nI The lift coefficient CL remains constant\nII The induced drag coefficient CDi decreases.", "options": [ { @@ -25555,8 +25555,8 @@ "explanation": "" }, "bVJPExo9": { - "id": "bVJPExo9", "type": "simple", + "id": "bVJPExo9", "question": "Which statement, about an aeroplane leaving ground effect at constant angle of attack, is correct? \nI The lift coefficient CL decreases\nII The induced drag coefficient CDi remains constant.", "options": [ { @@ -25592,12 +25592,12 @@ }, { "id": "QK2U50QRB3", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "YIx9qQjD": { - "id": "YIx9qQjD", "type": "simple", + "id": "YIx9qQjD", "question": "Which of the following occurs when trailing edge flaps are extended?", "options": [ { @@ -25633,12 +25633,12 @@ }, { "id": "QK5BSB50VJ", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "dFHwLQhC": { - "id": "dFHwLQhC", "type": "simple", + "id": "dFHwLQhC", "question": "Coefficient of Lift ( C~L~ ) is:", "options": [ { @@ -25674,12 +25674,12 @@ }, { "id": "QK8ASCBFB0", - "explanation": "", "learningObjectives": ["081.01.09.02.07"], + "explanation": "", "variants": { "dZIomsDM": { - "id": "dZIomsDM", "type": "simple", + "id": "dZIomsDM", "question": "After take-off the slats (when installed) are always retracted later than the flaps. Why?", "options": [ { @@ -25717,8 +25717,8 @@ "explanation": "" }, "6oZdBay7": { - "id": "6oZdBay7", "type": "simple", + "id": "6oZdBay7", "question": "After take-off the slats (when installed) are always retracted later than the flaps. Why?", "options": [ { @@ -25751,8 +25751,8 @@ "explanation": "" }, "4BoEthQM": { - "id": "4BoEthQM", "type": "simple", + "id": "4BoEthQM", "question": "After take-off the slats (when installed) are always retracted later than the flaps. Why?", "options": [ { @@ -25788,12 +25788,12 @@ }, { "id": "QKB3OXPJ61", - "explanation": "", "learningObjectives": ["081.01.05.02.02"], + "explanation": "", "variants": { "WJ52NJ0T": { - "id": "WJ52NJ0T", "type": "simple", + "id": "WJ52NJ0T", "question": "(For this question use the image in the annex). Assuming all bodies have the same cross-sectional area and are in motion, place these bodies in order of increasing pressure drag. The correct answer is:", "options": [ { @@ -25826,8 +25826,8 @@ "explanation": "" }, "PQxWGMvj": { - "id": "PQxWGMvj", "type": "simple", + "id": "PQxWGMvj", "question": "(For this question use the image in the annex). Assuming all bodies have the same cross-sectional area and are in motion, place these bodies in order of decreasing pressure drag. The correct answer is:", "options": [ { @@ -25863,12 +25863,12 @@ }, { "id": "QKBQLHR9B1", - "explanation": "", "learningObjectives": ["081.01.05.02.01"], + "explanation": "", "variants": { "r4SFcwAX": { - "id": "r4SFcwAX", "type": "simple", + "id": "r4SFcwAX", "question": "Parasite Drag can be divided into:1. Tip-vortex drag \n 2. Interference drag \n 3. Pressure drag \n 4. Friction dragThe combination that regroups all of the correct statements is:", "options": [ { @@ -25904,12 +25904,12 @@ }, { "id": "QKBTWP7EIK", - "explanation": "", "learningObjectives": ["081.01.04.02.03"], + "explanation": "", "variants": { "hBV1vZx7": { - "id": "hBV1vZx7", "type": "simple", + "id": "hBV1vZx7", "question": "When a wing’s angle of attack increases, the pressure differential (1) _____, leading to a/an (2) _____ in the intensity of the wing tip vortices.", "options": [ { @@ -25945,12 +25945,12 @@ }, { "id": "QKE1GN2SK2", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "GtrZE5ba": { - "id": "GtrZE5ba", "type": "simple", + "id": "GtrZE5ba", "question": "A symmetrical aerofoil in an airflow has a 2 degree angle of attack. Does it produce:", "options": [ { @@ -25983,8 +25983,8 @@ "explanation": "" }, "KLNuyfTr": { - "id": "KLNuyfTr", "type": "simple", + "id": "KLNuyfTr", "question": "A symmetrical aerofoil in an airflow has a 2 degree angle of attack. Does it produce:", "options": [ { @@ -26020,12 +26020,12 @@ }, { "id": "QKGXGX333H", - "explanation": "", "learningObjectives": ["081.01.09.01.05"], + "explanation": "", "variants": { "nQe5yrMA": { - "id": "nQe5yrMA", "type": "simple", + "id": "nQe5yrMA", "question": "Refer to figure. \n When compared to a clean configuration, the wing in the attached figure has a:", "options": [ { @@ -26061,12 +26061,12 @@ }, { "id": "QKKAQUE4B1", - "explanation": "", "learningObjectives": ["081.01.04.03.07"], + "explanation": "", "variants": { "Eii6piAd": { - "id": "Eii6piAd", "type": "simple", + "id": "Eii6piAd", "question": "Downwash increases when...", "options": [ { @@ -26102,12 +26102,12 @@ }, { "id": "QV83I2S1E7", - "explanation": "", "learningObjectives": ["081.01.05.07.05"], + "explanation": "", "variants": { "dL8m6D2F": { - "id": "dL8m6D2F", "type": "simple", + "id": "dL8m6D2F", "question": "Consider an aircraft flying in unaccelerated level flight in the non-stable region. What would be the result on Indicated Airspeed (IAS) and drag following a sudden decrease in aircraft speed with no change in thrust available?", "options": [ { @@ -26148,12 +26148,12 @@ }, { "id": "QKOT62B249", - "explanation": "", "learningObjectives": ["081.01.09.01.01"], + "explanation": "", "variants": { "2ovGDz35": { - "id": "2ovGDz35", "type": "simple", + "id": "2ovGDz35", "question": "(For this question use the image in the annex). Which type of flap is shown in the figure?", "options": [ { @@ -26189,12 +26189,12 @@ }, { "id": "QKR4KCUJVR", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "5VaM07es": { - "id": "5VaM07es", "type": "simple", + "id": "5VaM07es", "question": "How can the induced drag in a wing/aircraft be increased?", "options": [ { @@ -26230,12 +26230,12 @@ }, { "id": "QKRF69NXLK", - "explanation": "", "learningObjectives": ["081.01.12.01.02"], + "explanation": "", "variants": { "MfYY7Lhd": { - "id": "MfYY7Lhd", "type": "simple", + "id": "MfYY7Lhd", "question": "What is going to happen to the angle of attack, controllability and stall speed if an airplane encounters icing during flight?", "options": [ { @@ -26271,12 +26271,12 @@ }, { "id": "QKTIRCXJVN", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "fBGy7jKE": { - "id": "fBGy7jKE", "type": "simple", + "id": "fBGy7jKE", "question": "On a moderately cambered airfoil lift:", "options": [ { @@ -26312,12 +26312,12 @@ }, { "id": "QL0Z2CP98W", - "explanation": "", "learningObjectives": ["081.01.04.03.12"], + "explanation": "", "variants": { "5vGfWjXt": { - "id": "5vGfWjXt", "type": "simple", + "id": "5vGfWjXt", "question": "An aeroplane in flight has a C~L~ of 0.6. C~DI~ value is 0.1\nC~L~ is increased by a factor of 1.5. Calculate the new value of C~DI ~ ", "options": [ { @@ -26353,12 +26353,12 @@ }, { "id": "QL8YT7OIJ1", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "eJANmln8": { - "id": "eJANmln8", "type": "simple", + "id": "eJANmln8", "question": "An aeroplane is in level flight and has a coefficient of lift of 0.6 and a coefficient of induced drag of 0.1. The aircraft slows down while maintaining level flight. In order to maintain lift, the lift coefficient increases to 1.5. What is the new coefficient of induced drag?\n(Note: aircraft configuration remains constant)", "options": [ { @@ -26394,12 +26394,12 @@ }, { "id": "QLDMXSUK53", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "mJJCQJUh": { - "id": "mJJCQJUh", "type": "simple", + "id": "mJJCQJUh", "question": "Regarding a symmetric aerofoil section, which statements are correct or incorrect?\n1) The angle of attack is zero when the lift coefficient equals zero.\n2) The pitching moment is zero when the lift coefficient equals zero.", "options": [ { @@ -26435,12 +26435,12 @@ }, { "id": "QM7KB9E7ZJ", - "explanation": "", "learningObjectives": ["081.01.01.05.10"], + "explanation": "", "variants": { "RknqarEA": { - "id": "RknqarEA", "type": "simple", + "id": "RknqarEA", "question": "When a wing spoiler is extended at constant angle of attack:", "options": [ { @@ -26476,12 +26476,12 @@ }, { "id": "QLFS4PAMV6", - "explanation": "", "learningObjectives": ["081.01.04.03.12"], + "explanation": "", "variants": { "wuIenSPo": { - "id": "wuIenSPo", "type": "simple", + "id": "wuIenSPo", "question": "An aeroplane accelerates from 120 kts to 160 kts in level flight. The Parasite drag changes by a factor of ___ and the Induced drag coefficient changes by a factor of ___ .", "options": [ { @@ -26517,12 +26517,12 @@ }, { "id": "QLLG05H7QF", - "explanation": "", "learningObjectives": ["081.01.03.02.05"], + "explanation": "", "variants": { "GOvTIwRn": { - "id": "GOvTIwRn", "type": "simple", + "id": "GOvTIwRn", "question": "In low subsonic flight, the Lift Coefficient (CL) is affected by alpha and:", "options": [ { @@ -26558,12 +26558,12 @@ }, { "id": "QLNQ5Y904O", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "2Fyfec1Q": { - "id": "2Fyfec1Q", "type": "simple", + "id": "2Fyfec1Q", "question": "The Centre of Pressure of an aerofoil section is:", "options": [ { @@ -26599,12 +26599,12 @@ }, { "id": "QLP97YUOI4", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "zdwcF8MK": { - "id": "zdwcF8MK", "type": "simple", + "id": "zdwcF8MK", "question": "On an asymmetrical, single curve aerofoil, in subsonic airflow, at low angle of attack, when the angle of attack is increased, the centre of pressure will (assume a conventional transport aeroplane):", "options": [ { @@ -26640,12 +26640,12 @@ }, { "id": "QLQWK9O3FI", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "VWM7RnUk": { - "id": "VWM7RnUk", "type": "simple", + "id": "VWM7RnUk", "question": "A light aircraft is flying straight and level at 110 kts and a CL of 0.42. Calculate the new CL, if the pilot immediately pulls into a climb with a load factor of 2.2.\nCL~MAX~ = 1.1Aircraft mass = 1300 kg", "options": [ { @@ -26681,12 +26681,12 @@ }, { "id": "QLSLXS22OQ", - "explanation": "", "learningObjectives": ["081.01.02.02.02"], + "explanation": "", "variants": { "bIWyoHZb": { - "id": "bIWyoHZb", "type": "simple", + "id": "bIWyoHZb", "question": "With increasing angle of attack, the stagnation point will move ___ and the point of lowest pressure will move ___.", "options": [ { @@ -26722,12 +26722,12 @@ }, { "id": "QLUL9RSJ0J", - "explanation": "", "learningObjectives": ["081.01.01.04.03"], + "explanation": "", "variants": { "mIo588KI": { - "id": "mIo588KI", "type": "simple", + "id": "mIo588KI", "question": "Refer to the image\nMatch the letters identifying the airfoils with the corresponding numbers from the C~D~ graphic.", "options": [ { @@ -26763,12 +26763,12 @@ }, { "id": "QLV4WIKOJG", - "explanation": "", "learningObjectives": ["081.01.09.01.01"], + "explanation": "", "variants": { "Vc4CZh47": { - "id": "Vc4CZh47", "type": "simple", + "id": "Vc4CZh47", "question": "Which type of flap is shown in the picture 4?", "options": [ { @@ -26804,12 +26804,12 @@ }, { "id": "QLX6JT26HG", - "explanation": "", "learningObjectives": ["081.01.04.03.02"], + "explanation": "", "variants": { "ZLdIEozB": { - "id": "ZLdIEozB", "type": "simple", + "id": "ZLdIEozB", "question": "The induced drag coefficient, CD~i~ is proportional to:", "options": [ { @@ -26845,12 +26845,12 @@ }, { "id": "QLXF99AS0P", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "YdJLtso7": { - "id": "YdJLtso7", "type": "simple", + "id": "YdJLtso7", "question": "Which combination produces the least amount of induced drag?", "options": [ { @@ -26886,12 +26886,12 @@ }, { "id": "QLXN3VGURD", - "explanation": "", "learningObjectives": ["081.01.09.02.03"], + "explanation": "", "variants": { "Uxg7JUgO": { - "id": "Uxg7JUgO", "type": "simple", + "id": "Uxg7JUgO", "question": "When leading edge flaps are deployed,", "options": [ { @@ -26927,12 +26927,12 @@ }, { "id": "QLXXXQ4NAZ", - "explanation": "", "learningObjectives": ["081.01.01.05.01"], + "explanation": "", "variants": { "cxaCMHdS": { - "id": "cxaCMHdS", "type": "simple", + "id": "cxaCMHdS", "question": "The span-wise flow on an unswept wing is from the:", "options": [ { @@ -26968,12 +26968,12 @@ }, { "id": "QN01DFJCJQ", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "YVI8ulgq": { - "id": "YVI8ulgq", "type": "simple", + "id": "YVI8ulgq", "question": "Which of the following combinations will be most effective in reducing induced drag?", "options": [ { @@ -27009,12 +27009,12 @@ }, { "id": "QM17SE0K7F", - "explanation": "", "learningObjectives": ["081.01", "081.08"], + "explanation": "", "variants": { "xSFxKgVZ": { - "id": "xSFxKgVZ", "type": "simple", + "id": "xSFxKgVZ", "question": "Regarding downwash, which of the following answers is correct?", "options": [ { @@ -27050,12 +27050,12 @@ }, { "id": "QM1OCITM4G", - "explanation": "", "learningObjectives": ["081.01.01.01.01"], + "explanation": "", "variants": { "Ho6dYHxg": { - "id": "Ho6dYHxg", "type": "simple", + "id": "Ho6dYHxg", "question": "In SI units what are kilograms the unit of?", "options": [ { @@ -27091,12 +27091,12 @@ }, { "id": "QM81XWI1RI", - "explanation": "", "learningObjectives": ["081.01.02.01.01"], + "explanation": "", "variants": { "UCO348Hb": { - "id": "UCO348Hb", "type": "simple", + "id": "UCO348Hb", "question": "Refer to the image.\nWhat is the sequence that represents the ordering of the aerofoils by increasing C~L~ ?", "options": [ { @@ -27132,12 +27132,12 @@ }, { "id": "QMA8R3IWKP", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "cUW6py8L": { - "id": "cUW6py8L", "type": "simple", + "id": "cUW6py8L", "question": "Under what conditions would we see an increase in induced drag or a high induced drag?", "options": [ { @@ -27173,12 +27173,12 @@ }, { "id": "QMBQOWYLC7", - "explanation": "", "learningObjectives": ["081.01.01.01.03"], + "explanation": "", "variants": { "htSaiPrm": { - "id": "htSaiPrm", "type": "simple", + "id": "htSaiPrm", "question": "In general terms the kinetic energy of an object is dependent on:", "options": [ { @@ -27214,12 +27214,12 @@ }, { "id": "QMEYJH28YD", - "explanation": "", "learningObjectives": ["081.01.12.01.03"], + "explanation": "", "variants": { "MrBiZiEJ": { - "id": "MrBiZiEJ", "type": "simple", + "id": "MrBiZiEJ", "question": "Following de-icing on a foggy morning, you are in the takeoff roll and notice that you need more thrust than expected. What could be a cause of this?", "options": [ { @@ -27255,12 +27255,12 @@ }, { "id": "QMF882PX5M", - "explanation": "", "learningObjectives": ["081.01.09.01.01"], + "explanation": "", "variants": { "Cgsfpync": { - "id": "Cgsfpync", "type": "simple", + "id": "Cgsfpync", "question": "Which type of flap is shown in the picture 3?", "options": [ { @@ -27296,12 +27296,12 @@ }, { "id": "QMIWF5DM2M", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "evkLoINb": { - "id": "evkLoINb", "type": "simple", + "id": "evkLoINb", "question": "When the lift coefficient C~L~ of a negatively cambered aerofoil section is zero, the pitching moment is:", "options": [ { @@ -27334,8 +27334,8 @@ "explanation": "" }, "atxY7ct7": { - "id": "atxY7ct7", "type": "simple", + "id": "atxY7ct7", "question": "When the lift coefficient C~L~ of a symmetrical aerofoil section is zero, the pitching moment is:", "options": [ { @@ -27371,12 +27371,12 @@ }, { "id": "QMLMRQZFEA", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "gMssVpXz": { - "id": "gMssVpXz", "type": "simple", + "id": "gMssVpXz", "question": "The lift coefficient of an aerofoil section:", "options": [ { @@ -27412,12 +27412,12 @@ }, { "id": "QMOGGT4M8B", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "r6oGztQF": { - "id": "r6oGztQF", "type": "simple", + "id": "r6oGztQF", "question": "During slow flight, you would expect the forward stagnation point of a aerofoil to be at its...", "options": [ { @@ -27453,12 +27453,12 @@ }, { "id": "QMP0AUO3EP", - "explanation": "", "learningObjectives": ["081.01.12.01.03"], + "explanation": "", "variants": { "zCmMfSGR": { - "id": "zCmMfSGR", "type": "simple", + "id": "zCmMfSGR", "question": "The effect of tailplane icing can be to:", "options": [ { @@ -27494,12 +27494,12 @@ }, { "id": "QMROXJ7XOU", - "explanation": "", "learningObjectives": ["081.01.06.01.03"], + "explanation": "", "variants": { "KH7xCA7k": { - "id": "KH7xCA7k", "type": "simple", + "id": "KH7xCA7k", "question": "What will happen to the effective angle of attack when the aircraft enters ground effect?", "options": [ { @@ -27535,12 +27535,12 @@ }, { "id": "QMUGNNHXK8", - "explanation": "", "learningObjectives": ["081.01.03.02.02"], + "explanation": "", "variants": { "EYm5jkK3": { - "id": "EYm5jkK3", "type": "simple", + "id": "EYm5jkK3", "question": "The lift coefficient CL versus angle of attack curve of a negatively cambered aerofoil section intersects the vertical axis of the graph:", "options": [ { @@ -27573,8 +27573,8 @@ "explanation": "" }, "HycErXj8": { - "id": "HycErXj8", "type": "simple", + "id": "HycErXj8", "question": "The lift coefficient CL versus angle of attack curve of a positive cambered aerofoil section intersects the vertical axis of the graph:", "options": [ { @@ -27610,12 +27610,12 @@ }, { "id": "QMUJU3RFMG", - "explanation": "", "learningObjectives": ["081.01.06.01.01"], + "explanation": "", "variants": { "L6sXJtEu": { - "id": "L6sXJtEu", "type": "simple", + "id": "L6sXJtEu", "question": "Which statement about an aeroplane leaving ground effect is correct? \nI The downwash angle decreases\nII The induced angle of attack decreases.", "options": [ { @@ -27648,8 +27648,8 @@ "explanation": "" }, "4dXDffY3": { - "id": "4dXDffY3", "type": "simple", + "id": "4dXDffY3", "question": "Which statement about an aeroplane leaving ground effect is correct? \nI The downwash angle increases\nII The induced angle of attack decreases.", "options": [ { @@ -27682,8 +27682,8 @@ "explanation": "" }, "JK7beuod": { - "id": "JK7beuod", "type": "simple", + "id": "JK7beuod", "question": "Which statement about an aeroplane leaving ground effect is correct? \n\nI The downwash angle decreases\n II The induced angle of attack increases.", "options": [ { @@ -27716,8 +27716,8 @@ "explanation": "" }, "npo0Gz0v": { - "id": "npo0Gz0v", "type": "simple", + "id": "npo0Gz0v", "question": "Which statement about an aeroplane entering ground effect is correct? \n\nI The downwash angle decreases\n II The induced angle of attack increases.", "options": [ { @@ -27750,8 +27750,8 @@ "explanation": "" }, "mD7APuYh": { - "id": "mD7APuYh", "type": "simple", + "id": "mD7APuYh", "question": "Which statement about an aeroplane entering ground effect is correct? \nI The downwash angle increases\nII The induced angle of attack decreases.", "options": [ { @@ -27784,8 +27784,8 @@ "explanation": "" }, "dPX9Ac8B": { - "id": "dPX9Ac8B", "type": "simple", + "id": "dPX9Ac8B", "question": "Which statement about an aeroplane entering ground effect is correct? \n\nI The downwash angle increases\n II The induced angle of attack increases.", "options": [ { @@ -27818,8 +27818,8 @@ "explanation": "" }, "zVriXonw": { - "id": "zVriXonw", "type": "simple", + "id": "zVriXonw", "question": "Which statement about an aeroplane entering ground effect is correct? \nI The downwash angle decreases\nII The induced angle of attack decreases.", "options": [ { @@ -27855,12 +27855,12 @@ }, { "id": "QMUPH8D6BB", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "ftnegeK1": { - "id": "ftnegeK1", "type": "simple", + "id": "ftnegeK1", "question": "The Lift Coefficient versus Angle Of Attack curve of a symmetrical aerofoil section intersects the vertical axis of the graph...", "options": [ { @@ -27893,8 +27893,8 @@ "explanation": "" }, "8mvADRh0": { - "id": "8mvADRh0", "type": "simple", + "id": "8mvADRh0", "question": "The Lift Coefficient versus Angle Of Attack curve of a symmetrical aerofoil section intersects the horizontal axis of the graph...", "options": [ { @@ -27927,8 +27927,8 @@ "explanation": "" }, "KghT9ma6": { - "id": "KghT9ma6", "type": "simple", + "id": "KghT9ma6", "question": "The Lift Coefficient versus Angle Of Attack curve of a negatively cambered aerofoil section intersects the vertical axis of the graph...", "options": [ { @@ -27961,8 +27961,8 @@ "explanation": "" }, "SuARwKTy": { - "id": "SuARwKTy", "type": "simple", + "id": "SuARwKTy", "question": "The Lift Coefficient versus Angle Of Attack curve of a negatively cambered aerofoil section intersects the horizontal axis of the graph...", "options": [ { @@ -27995,8 +27995,8 @@ "explanation": "" }, "Je80pzRx": { - "id": "Je80pzRx", "type": "simple", + "id": "Je80pzRx", "question": "The Lift Coefficient versus Angle Of Attack curve of a positively cambered aerofoil section intersects the horizontal axis of the graph...", "options": [ { @@ -28029,8 +28029,8 @@ "explanation": "" }, "jDFiDo7Q": { - "id": "jDFiDo7Q", "type": "simple", + "id": "jDFiDo7Q", "question": "The Lift Coefficient versus Angle Of Attack curve of a positive cambered aerofoil section intersects the vertical axis of the graph...", "options": [ { @@ -28066,12 +28066,12 @@ }, { "id": "QN1ZN6SM6V", - "explanation": "", "learningObjectives": ["081.01.12.01.02"], + "explanation": "", "variants": { "jnnqNX9E": { - "id": "jnnqNX9E", "type": "simple", + "id": "jnnqNX9E", "question": "What type of drag is increased when an aerofoil is contaminated by dust and other particles?", "options": [ { @@ -28107,12 +28107,12 @@ }, { "id": "QN4EJWUZ7A", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "1qeHY5T2": { - "id": "1qeHY5T2", "type": "simple", + "id": "1qeHY5T2", "question": "The point on an airfoil where the airflow comes to rest is called the....and the pressure will be ..:......", "options": [ { @@ -28148,12 +28148,12 @@ }, { "id": "QN5AO1IX2X", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "nou2c3Wj": { - "id": "nou2c3Wj", "type": "simple", + "id": "nou2c3Wj", "question": "The point, where the aerodynamic lift acts on a wing is:", "options": [ { @@ -28194,12 +28194,12 @@ }, { "id": "QN5FWQPM6K", - "explanation": "", "learningObjectives": ["081.01.04.03.03"], + "explanation": "", "variants": { "sPJB5H8c": { - "id": "sPJB5H8c", "type": "simple", + "id": "sPJB5H8c", "question": "If the Aircraft is climbing at a constant 90 IAS, how Total Drag will vary if all other factors remain costant:", "options": [ { @@ -28232,8 +28232,8 @@ "explanation": "" }, "9EpALpZ2": { - "id": "9EpALpZ2", "type": "simple", + "id": "9EpALpZ2", "question": "If the Aircraft is climbing at a constant 90 IAS, how will Total Drag vary if all other factors remain constant:", "options": [ { @@ -28269,12 +28269,12 @@ }, { "id": "QN8NP6CR2R", - "explanation": "", "learningObjectives": ["081.01.01.03.08"], + "explanation": "", "variants": { "3oGX7doz": { - "id": "3oGX7doz", "type": "simple", + "id": "3oGX7doz", "question": "What increases the critical angle of attack? Use of", "options": [ { @@ -28310,12 +28310,12 @@ }, { "id": "QN9TPDCBCE", - "explanation": "", "learningObjectives": ["081.01.01.01.01"], + "explanation": "", "variants": { "Uqjq0UaA": { - "id": "Uqjq0UaA", "type": "simple", + "id": "Uqjq0UaA", "question": "The SI units of air density (I) and force (II) are:", "options": [ { @@ -28351,12 +28351,12 @@ }, { "id": "QNC6RUXS6E", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "H9l6Px7Q": { - "id": "H9l6Px7Q", "type": "simple", + "id": "H9l6Px7Q", "question": "What happens to the streamlines if speed is increased and level flight is maintained?", "options": [ { @@ -28392,12 +28392,12 @@ }, { "id": "QNCCO3QSIF", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "W4iv7Pup": { - "id": "W4iv7Pup", "type": "simple", + "id": "W4iv7Pup", "question": "An object has a drag of 785 N at sea level. Assuming ISA conditions and that the object is travelling at the same speed, calculate the drag of the object at 6 000 ft.", "options": [ { @@ -28433,12 +28433,12 @@ }, { "id": "QNDVZLPDSM", - "explanation": "", "learningObjectives": ["081.01.01.01.11"], + "explanation": "", "variants": { "kh4VX1QT": { - "id": "kh4VX1QT", "type": "simple", + "id": "kh4VX1QT", "question": "If the continuity equation is applicable, what will happen to the air density (rho) if the cross sectional area of a tube changes? (low speed, subsonic and incompressible flow)", "options": [ { @@ -28474,12 +28474,12 @@ }, { "id": "QNJXTA9UU6", - "explanation": "", "learningObjectives": ["081.01.06.01.03"], + "explanation": "", "variants": { "FlyJzhBZ": { - "id": "FlyJzhBZ", "type": "simple", + "id": "FlyJzhBZ", "question": "When entering ground effect, the following will occur:", "options": [ { @@ -28515,12 +28515,12 @@ }, { "id": "QNMUZL5511", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "8rtOOyyg": { - "id": "8rtOOyyg", "type": "simple", + "id": "8rtOOyyg", "question": "In straight and level flight at a speed of 1.3 V~S~, the lift coefficient, expressed as a percentage of its maximum (C~LMAX~), would be:", "options": [ { @@ -28553,8 +28553,8 @@ "explanation": "" }, "mPbchhci": { - "id": "mPbchhci", "type": "simple", + "id": "mPbchhci", "question": "In straight and level flight at a speed of 1.8 V~S~, the lift coefficient, expressed as a percentage of its maximum (C~LMAX~), would be:", "options": [ { @@ -28587,8 +28587,8 @@ "explanation": "" }, "SEZ0MUaR": { - "id": "SEZ0MUaR", "type": "simple", + "id": "SEZ0MUaR", "question": "In straight and level flight at a speed of 1.1 V~S~, the lift coefficient, expressed as a percentage of its maximum (C~LMAX~), would be:", "options": [ { @@ -28624,12 +28624,12 @@ }, { "id": "QNONK7AMRW", - "explanation": "", "learningObjectives": ["081.01.05.05.01"], + "explanation": "", "variants": { "kAG6dwhQ": { - "id": "kAG6dwhQ", "type": "simple", + "id": "kAG6dwhQ", "question": "Which line represents the total drag line of an aeroplane?", "options": [ { @@ -28665,12 +28665,12 @@ }, { "id": "QNVKVW4YZ7", - "explanation": "", "learningObjectives": ["081.01.01.01.09"], + "explanation": "", "variants": { "p1MueUTz": { - "id": "p1MueUTz", "type": "simple", + "id": "p1MueUTz", "question": "What is \"V\" In the dynamic pressure term (½rho V²) ?", "options": [ { @@ -28706,12 +28706,12 @@ }, { "id": "QNWHXZD2R9", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "ayyGwqQP": { - "id": "ayyGwqQP", "type": "simple", + "id": "ayyGwqQP", "question": "You are flying at 230 kts with a CL of 0.3. ATC instructs you to reduce the speed to 200 kts. What \n is the new CL?", "options": [ { @@ -28747,12 +28747,12 @@ }, { "id": "QNXIQC0FWW", - "explanation": "", "learningObjectives": ["081.01.09.03.01"], + "explanation": "", "variants": { "ieOOUULY": { - "id": "ieOOUULY", "type": "simple", + "id": "ieOOUULY", "question": "Vortex generators are fitted in front of control surfaces to:", "options": [ { @@ -28788,12 +28788,12 @@ }, { "id": "QNXTPCMI8N", - "explanation": "", "learningObjectives": ["081.01.09.01.08"], + "explanation": "", "variants": { "zOi3RnnF": { - "id": "zOi3RnnF", "type": "simple", + "id": "zOi3RnnF", "question": "When approaching to land, the pilot forgets to lower the flaps. What is going to happen to the LDR, drag and speed at threshold?", "options": [ { @@ -28829,12 +28829,12 @@ }, { "id": "QNYVHIEGGZ", - "explanation": "", "learningObjectives": ["081.01.09.02.07"], + "explanation": "", "variants": { "uuwiNqSx": { - "id": "uuwiNqSx", "type": "simple", + "id": "uuwiNqSx", "question": "The use of a slat in the leading edge of the wing enables the aeroplane to fly at a slower speed because:", "options": [ { @@ -28867,8 +28867,8 @@ "explanation": "" }, "IQAODHGX": { - "id": "IQAODHGX", "type": "simple", + "id": "IQAODHGX", "question": "The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because:", "options": [ { @@ -28901,8 +28901,8 @@ "explanation": "" }, "18mNJVEI": { - "id": "18mNJVEI", "type": "simple", + "id": "18mNJVEI", "question": "The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because:", "options": [ { @@ -28938,12 +28938,12 @@ }, { "id": "QNZKLM7P83", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "txWHb4YE": { - "id": "txWHb4YE", "type": "simple", + "id": "txWHb4YE", "question": "When speed is increased in straight and level flight on a positively cambered aerofoil, what happens to the:\n\n1. centre of pressure and2. the magnitude of the total lift force?", "options": [ { @@ -28979,12 +28979,12 @@ }, { "id": "QO2CRPYWN7", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "Qeni7zQ4": { - "id": "Qeni7zQ4", "type": "simple", + "id": "Qeni7zQ4", "question": "What will be the consequence on the speed of the aircraft while going from Point B to Point C and maintaining steady, straight and level flight?", "options": [ { @@ -29020,12 +29020,12 @@ }, { "id": "QO350GZP28", - "explanation": "", "learningObjectives": ["081.01.09.02.07"], + "explanation": "", "variants": { "qnUzzfYA": { - "id": "qnUzzfYA", "type": "simple", + "id": "qnUzzfYA", "question": "During take-off, the right slat does not extend. What might happen on rotation?", "options": [ { @@ -29061,12 +29061,12 @@ }, { "id": "QO3F1L9879", - "explanation": "", "learningObjectives": ["081.01.12.01.03"], + "explanation": "", "variants": { "NGGBjyRB": { - "id": "NGGBjyRB", "type": "simple", + "id": "NGGBjyRB", "question": "When landing an aircraft at an airfield during a hot day, the increased temperature of the runway will:", "options": [ { @@ -29102,12 +29102,12 @@ }, { "id": "QO46XZ9O90", - "explanation": "", "learningObjectives": ["081.01.04.03.07"], + "explanation": "", "variants": { "G49bRIo7": { - "id": "G49bRIo7", "type": "simple", + "id": "G49bRIo7", "question": "Which of the following statements about downwash is correct?", "options": [ { @@ -29143,12 +29143,12 @@ }, { "id": "QOA5WVG09W", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "vrAsoZju": { - "id": "vrAsoZju", "type": "simple", + "id": "vrAsoZju", "question": "On a un-swept wing, when the aerofoil is accelerated from subsonic to supersonic speeds, the aerodynamic centre", "options": [ { @@ -29184,12 +29184,12 @@ }, { "id": "QODTYSNMW7", - "explanation": "", "learningObjectives": ["081.01.01.01.01"], + "explanation": "", "variants": { "LDK6mjUY": { - "id": "LDK6mjUY", "type": "simple", + "id": "LDK6mjUY", "question": "What would the units expressed in Kgm/s² relate to?", "options": [ { @@ -29225,12 +29225,12 @@ }, { "id": "QOE0NS84IV", - "explanation": "", "learningObjectives": ["081.01.01.05.08"], + "explanation": "", "variants": { "FzHW4eHg": { - "id": "FzHW4eHg", "type": "simple", + "id": "FzHW4eHg", "question": "A high aspect ratio wing will:", "options": [ { @@ -29266,12 +29266,12 @@ }, { "id": "QOHBLWCBI7", - "explanation": "", "learningObjectives": ["081.01.09.03.01"], + "explanation": "", "variants": { "DKO2i8IN": { - "id": "DKO2i8IN", "type": "simple", + "id": "DKO2i8IN", "question": "What is the purpose of vortex generators?", "options": [ { @@ -29304,8 +29304,8 @@ "explanation": "" }, "FmsWjh6p": { - "id": "FmsWjh6p", "type": "simple", + "id": "FmsWjh6p", "question": "What is the purpose of vortex generators?", "options": [ { @@ -29341,12 +29341,12 @@ }, { "id": "QOHMMV886P", - "explanation": "", "learningObjectives": ["081.01.06.01.03"], + "explanation": "", "variants": { "8sjKV04J": { - "id": "8sjKV04J", "type": "simple", + "id": "8sjKV04J", "question": "Floating due to ground effect during an approach to land will occur:", "options": [ { @@ -29382,12 +29382,12 @@ }, { "id": "QOHY0TUTXI", - "explanation": "", "learningObjectives": ["081.01.09.01.06"], + "explanation": "", "variants": { "1TOo9j7t": { - "id": "1TOo9j7t", "type": "simple", + "id": "1TOo9j7t", "question": "When flaps are deployed at constant angle of attack the lift coefficient will", "options": [ { @@ -29423,12 +29423,12 @@ }, { "id": "QOK8YM238G", - "explanation": "", "learningObjectives": ["081.01.04.03.02"], + "explanation": "", "variants": { "6nSH30g6": { - "id": "6nSH30g6", "type": "simple", + "id": "6nSH30g6", "question": "The formula for induced drag is : Cdi = CL² / AR . AR is (1)........ and CL is (2)........", "options": [ { @@ -29464,12 +29464,12 @@ }, { "id": "QOLOZA19YA", - "explanation": "", "learningObjectives": ["081.01.03.02.01"], + "explanation": "", "variants": { "P1czW9Sn": { - "id": "P1czW9Sn", "type": "simple", + "id": "P1czW9Sn", "question": "The terms q and S in the lift formula are:", "options": [ { @@ -29505,12 +29505,12 @@ }, { "id": "QOOLUSYE0H", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "TzJ3EciD": { - "id": "TzJ3EciD", "type": "simple", + "id": "TzJ3EciD", "question": "Upon wing spoiler extension in straight and level flight, if the speed and load factor remain constant:", "options": [ { @@ -29546,12 +29546,12 @@ }, { "id": "QOP5IHE3Q0", - "explanation": "", "learningObjectives": ["081.01.06.01.03"], + "explanation": "", "variants": { "Zy7dGSsY": { - "id": "Zy7dGSsY", "type": "simple", + "id": "Zy7dGSsY", "question": "What happens to a wing's critical angle of attack when it enters ground effect?", "options": [ { @@ -29587,12 +29587,12 @@ }, { "id": "QOYG0LKBPL", - "explanation": "", "learningObjectives": ["081.01.01.01.06"], + "explanation": "", "variants": { "YbObN73m": { - "id": "YbObN73m", "type": "simple", + "id": "YbObN73m", "question": "If there is compressing of the air as occurs at higher speeds then:", "options": [ { @@ -29628,12 +29628,12 @@ }, { "id": "QOZDOV4O9Y", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "UyRrWsyk": { - "id": "UyRrWsyk", "type": "simple", + "id": "UyRrWsyk", "question": "Refer to the image.\nThe dotted line represents how a lift curve changes when a high-lift device is deployed. \nThis curve could apply to which of these devices?\nI. Krueger Flap\nII. Fowler flap\nIII. Slats and slots", "options": [ { @@ -29669,12 +29669,12 @@ }, { "id": "QP09YM3SCV", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "cJVAutTO": { - "id": "cJVAutTO", "type": "simple", + "id": "cJVAutTO", "question": "Considering the airflow around a positively cambered aerofoil that is producing lift, the point of minimum static pressure is found..", "options": [ { @@ -29707,8 +29707,8 @@ "explanation": "" }, "u9r5gnTi": { - "id": "u9r5gnTi", "type": "simple", + "id": "u9r5gnTi", "question": "Considering the airflow around a positively cambered aerofoil that is producing lift, the point of minimum static pressure is found...", "options": [ { @@ -29741,8 +29741,8 @@ "explanation": "" }, "R10i4g4V": { - "id": "R10i4g4V", "type": "simple", + "id": "R10i4g4V", "question": "Considering the airflow around a positively cambered aerofoil that is producing lift, the point of minimum static pressure is found...", "options": [ { @@ -29775,8 +29775,8 @@ "explanation": "" }, "3Z59BjCD": { - "id": "3Z59BjCD", "type": "simple", + "id": "3Z59BjCD", "question": "Considering the airflow around a positively cambered aerofoil that is producing lift, the point of minimum static pressure is found", "options": [ { @@ -29812,12 +29812,12 @@ }, { "id": "QP3RAH6U40", - "explanation": "", "learningObjectives": ["081.01.04.02.03"], + "explanation": "", "variants": { "t6dxKUXA": { - "id": "t6dxKUXA", "type": "simple", + "id": "t6dxKUXA", "question": "Wing-tip vortices are formed by the..", "options": [ { @@ -29853,12 +29853,12 @@ }, { "id": "QP67TYUBNV", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "m6DMCd0K": { - "id": "m6DMCd0K", "type": "simple", + "id": "m6DMCd0K", "question": "For a conventional, nose wheel aircraft configuration, the higher the Take-off Mass\n \n1) Range will decrease but endurance will increase. \n2) Gliding range will reduce. \n3) Stalling speed will increase. \n4) Stick forces at rotation will increase.\nSelect the combination of correct statements", "options": [ { @@ -29894,12 +29894,12 @@ }, { "id": "QP6G9C6YUD", - "explanation": "", "learningObjectives": ["081.01.01.01.01"], + "explanation": "", "variants": { "zlqpwug2": { - "id": "zlqpwug2", "type": "simple", + "id": "zlqpwug2", "question": "Newton metre (N m) is the SI unit of", "options": [ { @@ -29935,12 +29935,12 @@ }, { "id": "QP8GOOG3FY", - "explanation": "", "learningObjectives": ["081.01.10.01.02"], + "explanation": "", "variants": { "QzRJPl4P": { - "id": "QzRJPl4P", "type": "simple", + "id": "QzRJPl4P", "question": "Refer to figure 081-48.\nWhat will happen to the stall speed and AOA when extending spoilers?", "options": [ { @@ -29979,12 +29979,12 @@ }, { "id": "QPE8U4Q4QV", - "explanation": "", "learningObjectives": ["081.01.02.02.01"], + "explanation": "", "variants": { "iGl1A7Pr": { - "id": "iGl1A7Pr", "type": "simple", + "id": "iGl1A7Pr", "question": "The stagnation point moves up, what is the cause?", "options": [ { @@ -30020,12 +30020,12 @@ }, { "id": "QPG5BP2PVW", - "explanation": "", "learningObjectives": ["081.01.02.02.01"], + "explanation": "", "variants": { "ShwmE1UH": { - "id": "ShwmE1UH", "type": "simple", + "id": "ShwmE1UH", "question": "Stagnation Point moves up, what is the cause?", "options": [ { @@ -30061,12 +30061,12 @@ }, { "id": "QPG81E5PKQ", - "explanation": "", "learningObjectives": ["081.01.04.02.03"], + "explanation": "", "variants": { "bTq4EfVB": { - "id": "bTq4EfVB", "type": "simple", + "id": "bTq4EfVB", "question": "Which of these statements about the strength of wing tip vortices are correct or incorrect?\n1) Assuming no flow separation, the strength of wing tip vortices is not affected by angle of attack.\n2) The strength of wing tip vortices is not affected by aspect ratio.", "options": [ { @@ -30102,12 +30102,12 @@ }, { "id": "QPJZQCA60I", - "explanation": "", "learningObjectives": ["081.01.01.01.11"], + "explanation": "", "variants": { "B2mfs8kB": { - "id": "B2mfs8kB", "type": "simple", + "id": "B2mfs8kB", "question": "Bernoulli's equation can be written as:\n(P~T~ = total pressure, P~S~ = static pressure and q =dynamic pressure)", "options": [ { @@ -30143,12 +30143,12 @@ }, { "id": "QPKMTGGN80", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "11Ebe9SC": { - "id": "11Ebe9SC", "type": "simple", + "id": "11Ebe9SC", "question": "Which of the following factors reduces induced\ndrag?", "options": [ { @@ -30184,12 +30184,12 @@ }, { "id": "QPPFNF2W32", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "MgiwjBvR": { - "id": "MgiwjBvR", "type": "simple", + "id": "MgiwjBvR", "question": "What is correct regarding the effect of displacement drag and impingement drag on take-off performance? There is a (1) _____ effect in case of a rejected take-off and a (2) _____ effect for continued take-off.", "options": [ { @@ -30225,12 +30225,12 @@ }, { "id": "QPTIFOU5XW", - "explanation": "", "learningObjectives": ["081.01.02.01.02"], + "explanation": "", "variants": { "WoWWipgH": { - "id": "WoWWipgH", "type": "simple", + "id": "WoWWipgH", "question": "If in a two-dimensional incompressible and subsonic flow, the streamlines converge, the static pressure in the flow will:", "options": [ { @@ -30271,12 +30271,12 @@ }, { "id": "QPW2M2EBDD", - "explanation": "", "learningObjectives": ["081.01.05.05.01"], + "explanation": "", "variants": { "cHyB1wbq": { - "id": "cHyB1wbq", "type": "simple", + "id": "cHyB1wbq", "question": "(For this question use the image in the annex). Which line represents the total drag line of an aeroplane?", "options": [ { @@ -30312,12 +30312,12 @@ }, { "id": "QPXALDDW1G", - "explanation": "", "learningObjectives": ["081.01.04.02.08"], + "explanation": "", "variants": { "qYxUnygC": { - "id": "qYxUnygC", "type": "simple", + "id": "qYxUnygC", "question": "Regarding wake turbulence, choose the correct sentence.", "options": [ { @@ -30353,12 +30353,12 @@ }, { "id": "QPYM685TFE", - "explanation": "", "learningObjectives": ["081.01.04.02.02"], + "explanation": "", "variants": { "ObK4nMln": { - "id": "ObK4nMln", "type": "simple", + "id": "ObK4nMln", "question": "The span-wise flow is caused by the difference between the air pressure on top and beneath the wing and its direction of movement goes from:", "options": [ { @@ -30394,12 +30394,12 @@ }, { "id": "QPZVZFUUTU", - "explanation": "", "learningObjectives": ["081.01.02.09.02"], + "explanation": "", "variants": { "cmnobC5e": { - "id": "cmnobC5e", "type": "simple", + "id": "cmnobC5e", "question": "Refer to figure. \n The point in the annex showing zero lift is:", "options": [ { @@ -30435,12 +30435,12 @@ }, { "id": "QQ0O0TL960", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "UgSTAV4k": { - "id": "UgSTAV4k", "type": "simple", + "id": "UgSTAV4k", "question": "Refer to figure 081-33.\nWhich of the four points in the attached graph depicts the maximum lift to drag ratio?", "options": [ { @@ -30479,12 +30479,12 @@ }, { "id": "QQ52CUK5XF", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "6JECmelR": { - "id": "6JECmelR", "type": "simple", + "id": "6JECmelR", "question": "When trailing edge flaps are extended in level flight, the change in pitching moment, ignoring any effects on the tailplane, will be:", "options": [ { @@ -30520,12 +30520,12 @@ }, { "id": "QQ556CLSQJ", - "explanation": "", "learningObjectives": ["081.01.09.03.01"], + "explanation": "", "variants": { "tt4BR3sG": { - "id": "tt4BR3sG", "type": "simple", + "id": "tt4BR3sG", "question": "Vortex generators used as high lift devices are there\nto:", "options": [ { @@ -30561,12 +30561,12 @@ }, { "id": "QQ6C5DG4VU", - "explanation": "", "learningObjectives": ["081.01.09.01.06"], + "explanation": "", "variants": { "8JTOxRDY": { - "id": "8JTOxRDY", "type": "simple", + "id": "8JTOxRDY", "question": "The flaps are retracted and the angle of attack is maintained. What happens to the lift coefficient?", "options": [ { @@ -30602,12 +30602,12 @@ }, { "id": "QTF7EJZVTY", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "lHjjrvhR": { - "id": "lHjjrvhR", "type": "simple", + "id": "lHjjrvhR", "question": "Which of the following defines lift/drag ratio?", "options": [ { @@ -30640,8 +30640,8 @@ "explanation": "" }, "awR1VB9y": { - "id": "awR1VB9y", "type": "simple", + "id": "awR1VB9y", "question": "Which of the following defines lift/drag ratio?", "options": [ { @@ -30677,12 +30677,12 @@ }, { "id": "QQ8R30F9SD", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "8Vpmyhpg": { - "id": "8Vpmyhpg", "type": "simple", + "id": "8Vpmyhpg", "question": "An aircraft is in level flight maintaining 220Kts. C~L~ is 0.42.\nThe pilot starts a pull-up manoeuvre by increasing LF to 2.2.\nWhat is the new value of C~L~ ?", "options": [ { @@ -30718,12 +30718,12 @@ }, { "id": "QQ9YX71ZIH", - "explanation": "", "learningObjectives": ["081.01.04.03.03"], + "explanation": "", "variants": { "0URnx5mt": { - "id": "0URnx5mt", "type": "simple", + "id": "0URnx5mt", "question": "Given a constant load factor, which of these statements about the variation of induced drag with changes of speed and mass are correct or incorrect?\n\n1. When speed increases, induced drag decreases.\n\n2. When mass increases, induced drag increases.", "options": [ { @@ -30759,12 +30759,12 @@ }, { "id": "QQD2XO0ZZY", - "explanation": "", "learningObjectives": ["081.01.05.02.03"], + "explanation": "", "variants": { "sLkG2xzL": { - "id": "sLkG2xzL", "type": "simple", + "id": "sLkG2xzL", "question": "How may you decrease interference drag?", "options": [ { @@ -30800,12 +30800,12 @@ }, { "id": "QQDZ41VPR3", - "explanation": "", "learningObjectives": ["081.01.01.01.16"], + "explanation": "", "variants": { "BKNVhSfS": { - "id": "BKNVhSfS", "type": "simple", + "id": "BKNVhSfS", "question": "In a subsonic flow, the continuity equation states that, if the temperature of the flow through a stream tube rises, the speed of the flow", "options": [ { @@ -30841,12 +30841,12 @@ }, { "id": "QQNJY6LIEZ", - "explanation": "", "learningObjectives": ["081.01", "081.05"], + "explanation": "", "variants": { "FNrWnf42": { - "id": "FNrWnf42", "type": "simple", + "id": "FNrWnf42", "question": "In an aircraft fitted with spoilers for lateral control,\nand not deployed as speed brakes, a roll to the right is initiated\nby:", "options": [ { @@ -30879,8 +30879,8 @@ "explanation": "" }, "rdL8Up9a": { - "id": "rdL8Up9a", "type": "simple", + "id": "rdL8Up9a", "question": "In an aircraft fitted with spoilers for lateral control, and not deployed as speed brakes, a roll to the right is initiated by:", "options": [ { @@ -30916,12 +30916,12 @@ }, { "id": "QQODPFUQS3", - "explanation": "", "learningObjectives": ["081.01.04.03.03"], + "explanation": "", "variants": { "XRrEEtRO": { - "id": "XRrEEtRO", "type": "simple", + "id": "XRrEEtRO", "question": "Which statement is true regarding velocity and induced drag of an aerofoil?", "options": [ { @@ -30957,12 +30957,12 @@ }, { "id": "QQQJ5KHCQS", - "explanation": "", "learningObjectives": ["081.01.09.01.02"], + "explanation": "", "variants": { "vxvMHwY4": { - "id": "vxvMHwY4", "type": "simple", + "id": "vxvMHwY4", "question": "Cambered wing sections give ....(1).... maximum CL at\n....(2).... angles of attack.", "options": [ { @@ -30998,12 +30998,12 @@ }, { "id": "QQTYHO599A", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "saGjdQSj": { - "id": "saGjdQSj", "type": "simple", + "id": "saGjdQSj", "question": "What happens following the deployment of leading edge devices, while the trailing edge flaps remain retracted?", "options": [ { @@ -31039,12 +31039,12 @@ }, { "id": "QQX0I5YPZP", - "explanation": "", "learningObjectives": ["081.01.04.02.03"], + "explanation": "", "variants": { "xhdDkXE3": { - "id": "xhdDkXE3", "type": "simple", + "id": "xhdDkXE3", "question": "What could increase downwash behind a wing?", "options": [ { @@ -31080,12 +31080,12 @@ }, { "id": "QR2IX9MUUN", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "dZ2dqxlF": { - "id": "dZ2dqxlF", "type": "simple", + "id": "dZ2dqxlF", "question": "The speed of a light aircraft, which is flying straight and level, is 110 kt. Its C~L~ is 0.42. The pilot pulls for a climb with a load factor of 2.2. If C~L~ max is 1.1 and the mass of the aircraft is 1 300 kg, what is the new C~L~?", "options": [ { @@ -31121,12 +31121,12 @@ }, { "id": "QR6CWMSAFO", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "pbJQpdNl": { - "id": "pbJQpdNl", "type": "simple", + "id": "pbJQpdNl", "question": "Whilst maintaining straight and level flight with a lift coefficient C~L~ = 1, what will be the new approximate value of C~L~ after the speed is increased by 41%?", "options": [ { @@ -31162,12 +31162,12 @@ }, { "id": "QR92FLCRAS", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "MCprd9IJ": { - "id": "MCprd9IJ", "type": "simple", + "id": "MCprd9IJ", "question": "What is/are the force(s) acting on a symmetrical aerofoil element when the upstream airflow is parallel to the chord line?", "options": [ { @@ -31203,12 +31203,12 @@ }, { "id": "QR95M7V6CT", - "explanation": "", "learningObjectives": ["081.01.04.03.05"], + "explanation": "", "variants": { "DrOcM6Pb": { - "id": "DrOcM6Pb", "type": "simple", + "id": "DrOcM6Pb", "question": "What kind of drag will a fairing smoothening the angles where the wing meets the fuselage at the wing root reduce?", "options": [ { @@ -31244,12 +31244,12 @@ }, { "id": "QRHS45VCGF", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "CM1uz1rD": { - "id": "CM1uz1rD", "type": "simple", + "id": "CM1uz1rD", "question": "An aircraft is flying straight and level at 280 kt with a CL of 0.3. The crew are warned of turbulence ahead and reduce speed to 220 kts, the turbulence penetration speed for their aircraft. \n Determine the new value of CL:", "options": [ { @@ -31285,12 +31285,12 @@ }, { "id": "QRL4UV3B0W", - "explanation": "", "learningObjectives": ["081.01.09.01.08"], + "explanation": "", "variants": { "hJ7bs0ZY": { - "id": "hJ7bs0ZY", "type": "simple", + "id": "hJ7bs0ZY", "question": "When you have your flaps in clean configuration and lower the trailing edge flaps for takeoff configuration what happens to the airplane?", "options": [ { @@ -31326,12 +31326,12 @@ }, { "id": "QROHSFRK4Z", - "explanation": "", "learningObjectives": ["081.01.01.01.11"], + "explanation": "", "variants": { "74IfQpeA": { - "id": "74IfQpeA", "type": "simple", + "id": "74IfQpeA", "question": "Bernoulli's theorem states that:", "options": [ { @@ -31367,12 +31367,12 @@ }, { "id": "QRPRZHLEC7", - "explanation": "", "learningObjectives": ["081.01.01.05.08"], + "explanation": "", "variants": { "H2eaBw2a": { - "id": "H2eaBw2a", "type": "simple", + "id": "H2eaBw2a", "question": "Wing loading is the ratio of:", "options": [ { @@ -31408,12 +31408,12 @@ }, { "id": "QRSH57V6ZF", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "HAHsA5ho": { - "id": "HAHsA5ho", "type": "simple", + "id": "HAHsA5ho", "question": "An aircraft is flying at 230 kt with a coefficient of lift of 0.3. ATC request the pilot to slow down to 200 kt. What is the new coefficient of lift?", "options": [ { @@ -31446,8 +31446,8 @@ "explanation": "" }, "oEgV3Zf3": { - "id": "oEgV3Zf3", "type": "simple", + "id": "oEgV3Zf3", "question": "An aircraft is flying at 250 kt with a coefficient of lift of 0.3. ATC request the pilot to slow down to 200 kt. What is the new coefficient of lift?", "options": [ { @@ -31483,12 +31483,12 @@ }, { "id": "QRSXXWF1MN", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "6kwYr8wz": { - "id": "6kwYr8wz", "type": "simple", + "id": "6kwYr8wz", "question": "During the landing phase of flight, an aeroplane entering ground effect with a constant angle of attack will...", "options": [ { @@ -31521,8 +31521,8 @@ "explanation": "" }, "rVWJcJjh": { - "id": "rVWJcJjh", "type": "simple", + "id": "rVWJcJjh", "question": "During the landing phase of flight, an aeroplane entering ground effect with a constant angle of attack will", "options": [ { @@ -31555,8 +31555,8 @@ "explanation": "" }, "GcamHwzD": { - "id": "GcamHwzD", "type": "simple", + "id": "GcamHwzD", "question": "During the landing phase of flight, an aeroplane entering ground effect with a constant angle of attack will..", "options": [ { @@ -31592,12 +31592,12 @@ }, { "id": "QRW36GIU6A", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "iipCmvyZ": { - "id": "iipCmvyZ", "type": "simple", + "id": "iipCmvyZ", "question": "The drag of an aeroplane is 850 Newton. What is the new value of drag if wing surface area is increased by 10%?", "options": [ { @@ -31633,12 +31633,12 @@ }, { "id": "QRXWFVQ5PB", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "fLWslBEu": { - "id": "fLWslBEu", "type": "simple", + "id": "fLWslBEu", "question": "When an aeroplane is in ground effect:", "options": [ { @@ -31674,12 +31674,12 @@ }, { "id": "QS05ZG88VX", - "explanation": "", "learningObjectives": ["081.01.12.01.03"], + "explanation": "", "variants": { "xNfRhh6J": { - "id": "xNfRhh6J", "type": "simple", + "id": "xNfRhh6J", "question": "Your aircraft is de-iced in a section of an aerodrome with poor lighting. After takeoff you realise your climb gradient is lower than expected. What is the cause?", "options": [ { @@ -31715,12 +31715,12 @@ }, { "id": "QS50F06RZB", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "KhcFZOUh": { - "id": "KhcFZOUh", "type": "simple", + "id": "KhcFZOUh", "question": "In level flight, an aircraft has a C~L~ value of 0.35 at a speed of 1.6 VS. \n Determine the value of C~L~ if speed is reduced to 1.1 V~S~:", "options": [ { @@ -31756,12 +31756,12 @@ }, { "id": "QS7ONGWHOJ", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "OGKRRLyh": { - "id": "OGKRRLyh", "type": "simple", + "id": "OGKRRLyh", "question": "The force which acts at right angles to the relative airflow is:", "options": [ { @@ -31797,12 +31797,12 @@ }, { "id": "QSCLCCE6MP", - "explanation": "", "learningObjectives": ["081.01.02.06.03"], + "explanation": "", "variants": { "kijXfmSn": { - "id": "kijXfmSn", "type": "simple", + "id": "kijXfmSn", "question": "Which of the following is a cause of form drag on an object in high-speed airflow?", "options": [ { @@ -31838,12 +31838,12 @@ }, { "id": "QSDN3NHDSN", - "explanation": "", "learningObjectives": ["081.01.06.01.03"], + "explanation": "", "variants": { "VyELM9Cs": { - "id": "VyELM9Cs", "type": "simple", + "id": "VyELM9Cs", "question": "What will happen in ground effect?", "options": [ { @@ -31876,8 +31876,8 @@ "explanation": "" }, "K5xq6bl0": { - "id": "K5xq6bl0", "type": "simple", + "id": "K5xq6bl0", "question": "What will happen in ground effect?", "options": [ { @@ -31913,12 +31913,12 @@ }, { "id": "QSEILVVZU7", - "explanation": "", "learningObjectives": ["081.01.09.01.01"], + "explanation": "", "variants": { "AvSzQCbu": { - "id": "AvSzQCbu", "type": "simple", + "id": "AvSzQCbu", "question": "The type of flap which extends rearward from the trailing edge of the wing as it is lowered is called:", "options": [ { @@ -31954,12 +31954,12 @@ }, { "id": "QSHIJHJ7E8", - "explanation": "", "learningObjectives": ["081.01.01.04.04"], + "explanation": "", "variants": { "2yFo0sF0": { - "id": "2yFo0sF0", "type": "simple", + "id": "2yFo0sF0", "question": "Consider an aerofoil section. The relative thickness is the ratio of...", "options": [ { @@ -31995,12 +31995,12 @@ }, { "id": "QSLNKEPNF7", - "explanation": "", "learningObjectives": ["081.01.09.02.07"], + "explanation": "", "variants": { "EnANUw6g": { - "id": "EnANUw6g", "type": "simple", + "id": "EnANUw6g", "question": "When plain slats are deployed there is no change in the slope of the lift curve but", "options": [ { @@ -32036,12 +32036,12 @@ }, { "id": "QSMK8M23EX", - "explanation": "", "learningObjectives": ["081.01.01.01.11"], + "explanation": "", "variants": { "YNA9HNQw": { - "id": "YNA9HNQw", "type": "simple", + "id": "YNA9HNQw", "question": "Bernoulli stated that because the sum of all the energies in an airflow is constant, in a steady flow at low subsonic speeds, that:", "options": [ { @@ -32077,12 +32077,12 @@ }, { "id": "QSNNPTOYT2", - "explanation": "", "learningObjectives": ["081.01.04.03.02"], + "explanation": "", "variants": { "4KUGidjt": { - "id": "4KUGidjt", "type": "simple", + "id": "4KUGidjt", "question": "What is the definition of the Coefficient of Drag (C~D~ )?", "options": [ { @@ -32118,12 +32118,12 @@ }, { "id": "QST7926DAW", - "explanation": "", "learningObjectives": ["081.01.02.07.01"], + "explanation": "", "variants": { "z2xyidvA": { - "id": "z2xyidvA", "type": "simple", + "id": "z2xyidvA", "question": "Which statement is correct regarding C~L~ (lift coefficient) and alpha (angle of attack)?", "options": [ { @@ -32159,12 +32159,12 @@ }, { "id": "QSVRBGQTH9", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "QBTHlwIB": { - "id": "QBTHlwIB", "type": "simple", + "id": "QBTHlwIB", "question": "Extending trailing edge flaps will allow for ___ lift with ___ speed and ___ drag.", "options": [ { @@ -32200,12 +32200,12 @@ }, { "id": "QSXSLNZWFF", - "explanation": "", "learningObjectives": ["081.01.05.02.01"], + "explanation": "", "variants": { "mWuHKgt6": { - "id": "mWuHKgt6", "type": "simple", + "id": "mWuHKgt6", "question": "Which drag components make up parasite drag? 1. pressure drag. 2. friction drag. 3. induced drag. 4. interference drag. The combination that regroups all of the correct statements is:", "options": [ { @@ -32241,12 +32241,12 @@ }, { "id": "QSZ7GOXSM1", - "explanation": "", "learningObjectives": ["081.01.01.01.11"], + "explanation": "", "variants": { "bGXTpAU1": { - "id": "bGXTpAU1", "type": "simple", + "id": "bGXTpAU1", "question": "Bernoulli's equation can be written as (P~T~ = total pressure, P~S~ = static pressure, q = dynamic pressure):", "options": [ { @@ -32282,12 +32282,12 @@ }, { "id": "QSZGH8NC6O", - "explanation": "", "learningObjectives": ["081.01.03.02.02"], + "explanation": "", "variants": { "AO60ly3b": { - "id": "AO60ly3b", "type": "simple", + "id": "AO60ly3b", "question": "On a moderately cambered airfoil the centre of pressure\nmoves as alpha changes from zero lift alpha to about 10 degrees\nalpha. This movement is:", "options": [ { @@ -32323,12 +32323,12 @@ }, { "id": "QT19DX4L63", - "explanation": "", "learningObjectives": ["081.01.01.04.07"], + "explanation": "", "variants": { "rxkJLKPB": { - "id": "rxkJLKPB", "type": "simple", + "id": "rxkJLKPB", "question": "Which of the following describes the maximum camber of an aerofoil section?", "options": [ { @@ -32364,12 +32364,12 @@ }, { "id": "QT1HPCEM95", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "1AzDOBa4": { - "id": "1AzDOBa4", "type": "simple", + "id": "1AzDOBa4", "question": "A symmetrical aerofoil set at zero angle of attack in an air stream will produce:", "options": [ { @@ -32405,12 +32405,12 @@ }, { "id": "QT308DR7D8", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "wSCNN1eS": { - "id": "wSCNN1eS", "type": "simple", + "id": "wSCNN1eS", "question": "An aeroplane is taking off from an aerodrome where the take-off performance is limited by the runway length. Given the following information at which of the following heights will the value for induced drag (Cdi) be lowest? \nWing span: 20 m. \nAerodrome elevation: 52 ft. \nConsider NO changes in pitch attitude, speed, or wing configuration.", "options": [ { @@ -32446,12 +32446,12 @@ }, { "id": "QT6BMC03Y0", - "explanation": "", "learningObjectives": ["081.01.09.01.01"], + "explanation": "", "variants": { "XjG8Ho3U": { - "id": "XjG8Ho3U", "type": "simple", + "id": "XjG8Ho3U", "question": "Refer to figure. \n Which type of flap is shown in the picture 3?", "options": [ { @@ -32484,8 +32484,8 @@ "explanation": "" }, "IB2rFiB6": { - "id": "IB2rFiB6", "type": "simple", + "id": "IB2rFiB6", "question": "Refer to figure. \n Which type of flap is shown in the picture 4?", "options": [ { @@ -32521,12 +32521,12 @@ }, { "id": "QT92RXEFNB", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "ldet2qM8": { - "id": "ldet2qM8", "type": "simple", + "id": "ldet2qM8", "question": "The pilot flying an aircraft extends the trailing edge flaps. This will allow for a (1) _____ lift, with (2) _____ speed and (3) _____ drag.", "options": [ { @@ -32562,12 +32562,12 @@ }, { "id": "QT9QYHLH6A", - "explanation": "", "learningObjectives": ["081.01.04.03.04"], + "explanation": "", "variants": { "IWTU715F": { - "id": "IWTU715F", "type": "simple", + "id": "IWTU715F", "question": "To generate a constant lift force, any adjustment in IAS must be met with an adjustment in: ", "options": [ { @@ -32603,12 +32603,12 @@ }, { "id": "QT9SOYUKVE", - "explanation": "", "learningObjectives": ["081.01.01.01.11"], + "explanation": "", "variants": { "7fKMJpZb": { - "id": "7fKMJpZb", "type": "simple", + "id": "7fKMJpZb", "question": "Bernoulli's equation is: \n(Note: Rho = actual density; Pstat = static pressure; Pdyn = dynamic pressure; Ptot = total pressure; * is to 'multiply by')", "options": [ { @@ -32644,12 +32644,12 @@ }, { "id": "QTAIDNBIXG", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "QNO2iEU2": { - "id": "QNO2iEU2", "type": "simple", + "id": "QNO2iEU2", "question": "Consider two otherwise equal aircraft, but one has larger winglets than the other. In the aircraft with the larger winglets, ground effect is expected to:", "options": [ { @@ -32685,12 +32685,12 @@ }, { "id": "QTBTZEUAV0", - "explanation": "", "learningObjectives": ["081.01.01.05.12"], + "explanation": "", "variants": { "Xy1glXvi": { - "id": "Xy1glXvi", "type": "simple", + "id": "Xy1glXvi", "question": "The wing angle of incidence usually varies from root to tip. This is called wing washout and its purpose is...", "options": [ { @@ -32726,12 +32726,12 @@ }, { "id": "QWJBOE9AFR", - "explanation": "", "learningObjectives": ["081.01.09.02.02"], + "explanation": "", "variants": { "Bbsy1Jed": { - "id": "Bbsy1Jed", "type": "simple", + "id": "Bbsy1Jed", "question": "Slat extension will:", "options": [ { @@ -32770,8 +32770,8 @@ "explanation": "" }, "VbBSgK3a": { - "id": "VbBSgK3a", "type": "simple", + "id": "VbBSgK3a", "question": "Slat extension will:", "options": [ { @@ -32807,12 +32807,12 @@ }, { "id": "QTFZ64SLX6", - "explanation": "", "learningObjectives": ["081.01.12.02.02"], + "explanation": "", "variants": { "VPvCyO3B": { - "id": "VPvCyO3B", "type": "simple", + "id": "VPvCyO3B", "question": "With reference to the skin of an aircraft - which drag is going to increase with increasing age?", "options": [ { @@ -32848,12 +32848,12 @@ }, { "id": "QTHAVVVOD4", - "explanation": "", "learningObjectives": ["081.01.05.01.01"], + "explanation": "", "variants": { "56HaeZuK": { - "id": "56HaeZuK", "type": "simple", + "id": "56HaeZuK", "question": "Which statement, about the effects on drag of fitting external tip tanks to the wings of an aeroplane, is correct? \n\nI Parasite drag increases\n II Induced drag increases.", "options": [ { @@ -32886,8 +32886,8 @@ "explanation": "" }, "Qq910o9L": { - "id": "Qq910o9L", "type": "simple", + "id": "Qq910o9L", "question": "Which statement, about the effects on drag of fitting external tip tanks to the wings of an aeroplane, is correct? \n\nI Parasite drag increases\n II Induced drag decreases.", "options": [ { @@ -32920,8 +32920,8 @@ "explanation": "" }, "n4LKIfb6": { - "id": "n4LKIfb6", "type": "simple", + "id": "n4LKIfb6", "question": "Which statement, about the effects on drag of fitting external tip tanks to the wings of an aeroplane, is correct?\n I Parasite drag decreases\n II Induced drag decreases.", "options": [ { @@ -32957,12 +32957,12 @@ }, { "id": "QTI2LXZH0M", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "T0129CHh": { - "id": "T0129CHh", "type": "simple", + "id": "T0129CHh", "question": "On a highly swept back wing with leading edge flaps and leading edge slats, which device would be fitted in the following locations?", "options": [ { @@ -32998,12 +32998,12 @@ }, { "id": "QTIQTZO18E", - "explanation": "", "learningObjectives": ["081.01.09.01.05"], + "explanation": "", "variants": { "NQXXMDlA": { - "id": "NQXXMDlA", "type": "simple", + "id": "NQXXMDlA", "question": "A plane is flying at 1,8 Vs, what % of C~LMAX~ is that?", "options": [ { @@ -33039,12 +33039,12 @@ }, { "id": "QTJV3DYPCM", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "JghfpFXu": { - "id": "JghfpFXu", "type": "simple", + "id": "JghfpFXu", "question": "Example question: An aircraft is flying straight and level at 280kts with a C~L~ of 0.3.\nThe crew are warned of turbulence ahead and reduce speed to 220kts, the turbulence penetration speed for their aircraft. \nWhat is the new value of C~L~ ?\r \r \r \r \r ", "options": [ { @@ -33080,12 +33080,12 @@ }, { "id": "QTLI3G3QOV", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "aRa58nKg": { - "id": "aRa58nKg", "type": "simple", + "id": "aRa58nKg", "question": "In straight and level flight, which sentence is correct regarding the C~L~/C~D~ ratio?", "options": [ { @@ -33121,12 +33121,12 @@ }, { "id": "QTNAXMDDMY", - "explanation": "", "learningObjectives": ["081.01.04.03.05"], + "explanation": "", "variants": { "jSyLqEfO": { - "id": "jSyLqEfO", "type": "simple", + "id": "jSyLqEfO", "question": "Methods to reduce induced drag include:", "options": [ { @@ -33162,12 +33162,12 @@ }, { "id": "QTOFSA1KZL", - "explanation": "", "learningObjectives": ["081.01.01.05.05"], + "explanation": "", "variants": { "MYnAya1o": { - "id": "MYnAya1o", "type": "simple", + "id": "MYnAya1o", "question": "Refer to figure 081-46.\nSelect the wing profile(s) that matches the graph:", "options": [ { @@ -33206,12 +33206,12 @@ }, { "id": "QTOMG9F3XN", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "YxezWECB": { - "id": "YxezWECB", "type": "simple", + "id": "YxezWECB", "question": "What will the extension of the leading-edge flaps result in?", "options": [ { @@ -33247,12 +33247,12 @@ }, { "id": "QTONUBYCX8", - "explanation": "", "learningObjectives": ["081.01", "081.08"], + "explanation": "", "variants": { "kTNw0NMZ": { - "id": "kTNw0NMZ", "type": "simple", + "id": "kTNw0NMZ", "question": "The lift formula is:\n(rho = density)", "options": [ { @@ -33285,8 +33285,8 @@ "explanation": "" }, "0TY7HeMG": { - "id": "0TY7HeMG", "type": "simple", + "id": "0TY7HeMG", "question": "The lift formula is:\n (rho = density)", "options": [ { @@ -33322,12 +33322,12 @@ }, { "id": "QYBEC8MU2L", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "hTDzbcXC": { - "id": "hTDzbcXC", "type": "simple", + "id": "hTDzbcXC", "question": "An airliner with swept back wings is equipped with slats and/or leading edge (LE) flaps. The usual arrangement on the leading edge is:", "options": [ { @@ -33363,12 +33363,12 @@ }, { "id": "QTT7S08WRJ", - "explanation": "", "learningObjectives": ["081.01.12.01.03"], + "explanation": "", "variants": { "VqKaGzDS": { - "id": "VqKaGzDS", "type": "simple", + "id": "VqKaGzDS", "question": "An aircraft is configured for take-off and about to take-off. If the slats on the right wing remained retracted, what are the possible consequences?", "options": [ { @@ -33404,12 +33404,12 @@ }, { "id": "QTUD3L5SHL", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "e6paiZKH": { - "id": "e6paiZKH", "type": "simple", + "id": "e6paiZKH", "question": "When the lift coefficient of a symmetrical aerofoil section is zero, the pitching moment is...", "options": [ { @@ -33442,8 +33442,8 @@ "explanation": "" }, "dLIaj3p4": { - "id": "dLIaj3p4", "type": "simple", + "id": "dLIaj3p4", "question": "When the lift coefficient of a positively cambered aerofoil section is zero, the pitching moment is...", "options": [ { @@ -33476,8 +33476,8 @@ "explanation": "" }, "qMNpWmD4": { - "id": "qMNpWmD4", "type": "simple", + "id": "qMNpWmD4", "question": "When the lift coefficient of a negatively cambered aerofoil section is zero, the pitching moment is...", "options": [ { @@ -33513,12 +33513,12 @@ }, { "id": "QTUSIQJCUZ", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "Ecy2pYCo": { - "id": "Ecy2pYCo", "type": "simple", + "id": "Ecy2pYCo", "question": "What happens when the trailing edge flaps are lowered to the fully extended position?", "options": [ { @@ -33554,12 +33554,12 @@ }, { "id": "QTVLDACQBE", - "explanation": "", "learningObjectives": ["081.01.01.05.12"], + "explanation": "", "variants": { "hJBpNWlk": { - "id": "hJBpNWlk", "type": "simple", + "id": "hJBpNWlk", "question": "An aeroplane's wing angle of incidence is defined as the angle between the:", "options": [ { @@ -33595,12 +33595,12 @@ }, { "id": "QTWGEGJ022", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "eA844iaV": { - "id": "eA844iaV", "type": "simple", + "id": "eA844iaV", "question": "Which statement about the centre of pressure and aerodynamic centre of an asymmetrical airfoil is true for an aerofoil with a low angle of attack?", "options": [ { @@ -33636,12 +33636,12 @@ }, { "id": "QTX947M4UD", - "explanation": "", "learningObjectives": ["081.01.04.03.15"], + "explanation": "", "variants": { "umZ5UXp1": { - "id": "umZ5UXp1", "type": "simple", + "id": "umZ5UXp1", "question": "The best L/D ratio is usually found when you have:", "options": [ { @@ -33677,12 +33677,12 @@ }, { "id": "QTZ0GPL19Q", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "zu3v7rYz": { - "id": "zu3v7rYz", "type": "simple", + "id": "zu3v7rYz", "question": "The point of minimum static pressure on a positively cambered aerofoil flying at a low subsonic speeds at a positive angle of attack is...", "options": [ { @@ -33718,12 +33718,12 @@ }, { "id": "QU0169GO5T", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "cmWpXd6v": { - "id": "cmWpXd6v", "type": "simple", + "id": "cmWpXd6v", "question": "A Krueger flap is normally located at the", "options": [ { @@ -33759,12 +33759,12 @@ }, { "id": "QU3WPZMHCV", - "explanation": "", "learningObjectives": ["081.01", "081.03"], + "explanation": "", "variants": { "4sOb8iCH": { - "id": "4sOb8iCH", "type": "simple", + "id": "4sOb8iCH", "question": "An aeroplane stalls due to excessive:", "options": [ { @@ -33800,12 +33800,12 @@ }, { "id": "QUARQV8IM1", - "explanation": "", "learningObjectives": ["081.01.06.01.01"], + "explanation": "", "variants": { "EfxAq7b9": { - "id": "EfxAq7b9", "type": "simple", + "id": "EfxAq7b9", "question": "Which statements about an aeroplane entering ground effect are correct or incorrect?\n1) The downwash angle remains constant.\n2) The induced angle of attack increases.", "options": [ { @@ -33838,8 +33838,8 @@ "explanation": "" }, "HOvGFad7": { - "id": "HOvGFad7", "type": "simple", + "id": "HOvGFad7", "question": "Which statements about an aeroplane entering ground effect are correct or incorrect?\n1) The downwash angle increases.\n2) The induced angle of attack remains constant.", "options": [ { @@ -33872,8 +33872,8 @@ "explanation": "" }, "9jjt3VOa": { - "id": "9jjt3VOa", "type": "simple", + "id": "9jjt3VOa", "question": "Which statements about an aeroplane entering ground effect are correct or incorrect?\n1) The downwash angle decreases.\n2) The induced angle of attack remains constant.", "options": [ { @@ -33906,8 +33906,8 @@ "explanation": "" }, "MqEq2gJ5": { - "id": "MqEq2gJ5", "type": "simple", + "id": "MqEq2gJ5", "question": "Which statements about an aeroplane entering ground effect are correct or incorrect?\n1) The downwash angle remains constant.\n2) The induced angle of attack decreases.", "options": [ { @@ -33940,8 +33940,8 @@ "explanation": "" }, "lJf7i9Vz": { - "id": "lJf7i9Vz", "type": "simple", + "id": "lJf7i9Vz", "question": "Which statements about an aeroplane leaving ground effect are correct or incorrect?\n1) The downwash angle remains constant.\n2) The induced angle of attack increases.", "options": [ { @@ -33974,8 +33974,8 @@ "explanation": "" }, "EFuMUmdM": { - "id": "EFuMUmdM", "type": "simple", + "id": "EFuMUmdM", "question": "Which statements about an aeroplane leaving ground effect are correct or incorrect?\n1) The downwash angle increases.\n2) The induced angle of attack remains constant.", "options": [ { @@ -34008,8 +34008,8 @@ "explanation": "" }, "osJsXh34": { - "id": "osJsXh34", "type": "simple", + "id": "osJsXh34", "question": "Which statements about an aeroplane leaving ground effect are correct or incorrect?\n1) The downwash angle remains constant.\n2) The induced angle of attack decreases.", "options": [ { @@ -34045,12 +34045,12 @@ }, { "id": "QULCZZFUPX", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "RymWTTrZ": { - "id": "RymWTTrZ", "type": "simple", + "id": "RymWTTrZ", "question": "When landing an aircraft an airfield during a hot day, the increased temperature of the runway will:", "options": [ { @@ -34086,12 +34086,12 @@ }, { "id": "QUMB66YFNQ", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "rrIilUmr": { - "id": "rrIilUmr", "type": "simple", + "id": "rrIilUmr", "question": "Comparing the lift coefficient and drag coefficient for conventional aeroplanes at normal angle of attack:", "options": [ { @@ -34127,12 +34127,12 @@ }, { "id": "QUPXJVIHCF", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "27NGAiB8": { - "id": "27NGAiB8", "type": "simple", + "id": "27NGAiB8", "question": "For this question refer to the image. The lower red line represents a wing in the clean situation, and the upper blue line represents the same wing with a lift augmentation device extended. What is the basic wing profile and what type of lift augmentatin device is used.", "options": [ { @@ -34168,12 +34168,12 @@ }, { "id": "QUS7CD28V8", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "jFkm0ffT": { - "id": "jFkm0ffT", "type": "simple", + "id": "jFkm0ffT", "question": "Refer to the image.\nIf the trailing edge flaps are stuck in the position shown in the picture, the pilot would have to:", "options": [ { @@ -34209,12 +34209,12 @@ }, { "id": "QUUQGA6KKH", - "explanation": "", "learningObjectives": ["081.01.03.02.01"], + "explanation": "", "variants": { "NfQXOV8c": { - "id": "NfQXOV8c", "type": "simple", + "id": "NfQXOV8c", "question": "The two main methods for increasing lift are:", "options": [ { @@ -34250,12 +34250,12 @@ }, { "id": "QUY13EY7WB", - "explanation": "", "learningObjectives": ["081.01.04.03.06"], + "explanation": "", "variants": { "HwSP5Aba": { - "id": "HwSP5Aba", "type": "simple", + "id": "HwSP5Aba", "question": "Which of these statements about induced drag are correct or incorrect?\n1) A rectangular spanwise lift distribution generates more induced drag than an elliptical lift distribution.\n2) Induced drag decreases with increasing aspect ratio.", "options": [ { @@ -34288,8 +34288,8 @@ "explanation": "" }, "bRqLFNRC": { - "id": "bRqLFNRC", "type": "simple", + "id": "bRqLFNRC", "question": "Which of these statements about induced drag are correct or incorrect?\n1) A rectangular spanwise lift distribution generates more induced drag than an elliptical lift distribution.\n2) Induced drag increases with increasing aspect ratio.", "options": [ { @@ -34322,8 +34322,8 @@ "explanation": "" }, "YdsxlZR9": { - "id": "YdsxlZR9", "type": "simple", + "id": "YdsxlZR9", "question": "Which of these statements about induced drag are correct or incorrect?\n1) A rectangular spanwise lift distribution generates less induced drag than an elliptical lift distribution.\n2) Induced drag decreases with increasing aspect ratio.", "options": [ { @@ -34356,8 +34356,8 @@ "explanation": "" }, "pe2w0WqC": { - "id": "pe2w0WqC", "type": "simple", + "id": "pe2w0WqC", "question": "Which of these statements about induced drag are correct or incorrect?\n1) A rectangular spanwise lift distribution generates less induced drag than an elliptical lift distribution.\n2) Induced drag increases with increasing aspect ratio.", "options": [ { @@ -34390,8 +34390,8 @@ "explanation": "" }, "4PGZLF3S": { - "id": "4PGZLF3S", "type": "simple", + "id": "4PGZLF3S", "question": "Which of these statements about induced drag are correct or incorrect?\n1) An elliptical spanwise lift distribution generates more induced drag than a rectangular lift distribution.\n2) Induced drag increases with decreasing aspect ratio.", "options": [ { @@ -34424,8 +34424,8 @@ "explanation": "" }, "qnpGYram": { - "id": "qnpGYram", "type": "simple", + "id": "qnpGYram", "question": "Which of these statements about induced drag are correct or incorrect?\n1) An elliptical spanwise lift distribution generates more induced drag than a rectangular lift distribution.\n2) Induced drag decreases with decreasing aspect ratio.", "options": [ { @@ -34458,8 +34458,8 @@ "explanation": "" }, "OJDW41VA": { - "id": "OJDW41VA", "type": "simple", + "id": "OJDW41VA", "question": "Which of these statements about induced drag are correct or incorrect?\n1) An elliptical spanwise lift distribution generates less induced drag than a rectangular lift distribution.\n2) Induced drag decreases with decreasing aspect ratio.", "options": [ { @@ -34492,8 +34492,8 @@ "explanation": "" }, "Oz0c4ncn": { - "id": "Oz0c4ncn", "type": "simple", + "id": "Oz0c4ncn", "question": "Which of these statements about induced drag are correct or incorrect?\n1) An elliptical spanwise lift distribution generates less induced drag than a rectangular lift distribution.\n2) Induced drag increases with decreasing aspect ratio.", "options": [ { @@ -34529,12 +34529,12 @@ }, { "id": "QUZ4QYM201", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "AvhmVvke": { - "id": "AvhmVvke", "type": "simple", + "id": "AvhmVvke", "question": "At which point is the static pressure lowest on an aerofoil?", "options": [ { @@ -34570,12 +34570,12 @@ }, { "id": "QV1Q6L8IW9", - "explanation": "", "learningObjectives": ["081.01.01.05.09"], + "explanation": "", "variants": { "wf3oMgoH": { - "id": "wf3oMgoH", "type": "simple", + "id": "wf3oMgoH", "question": "Dihedral of a wing is the angle between:", "options": [ { @@ -34608,8 +34608,8 @@ "explanation": "" }, "8uQAdxYT": { - "id": "8uQAdxYT", "type": "simple", + "id": "8uQAdxYT", "question": "Dihedral of a wing is the angle between:", "options": [ { @@ -34645,12 +34645,12 @@ }, { "id": "QVTD2GX25Y", - "explanation": "", "learningObjectives": ["081.01.02.03.01"], + "explanation": "", "variants": { "WQPfOs9d": { - "id": "WQPfOs9d", "type": "simple", + "id": "WQPfOs9d", "question": "Where the airflow over a wing coverges, the effect on pressure and airflow speed is:", "options": [ { @@ -34686,12 +34686,12 @@ }, { "id": "QV32TDH9R2", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "uUtVMQNn": { - "id": "uUtVMQNn", "type": "simple", + "id": "uUtVMQNn", "question": "Which statement is true regarding a reduction in induced drag?", "options": [ { @@ -34727,12 +34727,12 @@ }, { "id": "QVBA8KLDIG", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "E5WoJ1tR": { - "id": "E5WoJ1tR", "type": "simple", + "id": "E5WoJ1tR", "question": "Regarding a symmetric aerofoil section, which statements are correct or incorrect?\n1) The angle of attack has a positive value when the lift coefficient equals zero.\n2) A nose down pitching moment exists when the lift coefficient equals zero.", "options": [ { @@ -34765,8 +34765,8 @@ "explanation": "" }, "M2YOjS5A": { - "id": "M2YOjS5A", "type": "simple", + "id": "M2YOjS5A", "question": "Regarding a positively cambered aerofoil section, which statements are correct or incorrect?\n1) The angle of attack has a positive value when the lift coefficient equals zero.\n2) A nose down pitching moment exists when the lift coefficient equals zero.", "options": [ { @@ -34799,8 +34799,8 @@ "explanation": "" }, "GvM4h6Zg": { - "id": "GvM4h6Zg", "type": "simple", + "id": "GvM4h6Zg", "question": "Regarding a positively cambered aerofoil section, which statements are correct or incorrect?\n1) The angle of attack has a negative value when the lift coefficient equals zero.\n2) A nose down pitching moment exists when the lift coefficient equals zero.", "options": [ { @@ -34836,12 +34836,12 @@ }, { "id": "QVEN8BFS7I", - "explanation": "", "learningObjectives": ["081.01.09.01.09"], + "explanation": "", "variants": { "SnYuuYti": { - "id": "SnYuuYti", "type": "simple", + "id": "SnYuuYti", "question": "Before takeoff, the pilot decides for an an intermediate flap setting due to climb performance. After engine start, a greater flap setting is selected by mistake. In these circumstances, the rotation speed will be (1) _____ and climb performance will be (2) _____.", "options": [ { @@ -34877,12 +34877,12 @@ }, { "id": "QVF5KXIM5Z", - "explanation": "", "learningObjectives": ["081.01.01.01.01"], + "explanation": "", "variants": { "T9uRCwPs": { - "id": "T9uRCwPs", "type": "simple", + "id": "T9uRCwPs", "question": "What is the SI unit for the weight of an aeroplane or helicopter?", "options": [ { @@ -34918,12 +34918,12 @@ }, { "id": "QVLMOYDSOE", - "explanation": "", "learningObjectives": ["081.01", "081.02"], + "explanation": "", "variants": { "MUpKq93i": { - "id": "MUpKq93i", "type": "simple", + "id": "MUpKq93i", "question": "Which design characteristic is typical for a supercritical aerofoil when compared to a conventional positive-cambered aerofoil?", "options": [ { @@ -34959,12 +34959,12 @@ }, { "id": "QVQF6ZFO02", - "explanation": "", "learningObjectives": ["081.01.04.03.04"], + "explanation": "", "variants": { "2g8Fe3vz": { - "id": "2g8Fe3vz", "type": "simple", + "id": "2g8Fe3vz", "question": "For an aircraft flying straight and level at constant IAS, when flaps are extended the induced drag:", "options": [ { @@ -35000,12 +35000,12 @@ }, { "id": "QW0E2YLRLO", - "explanation": "", "learningObjectives": ["081.01.04.03.10"], + "explanation": "", "variants": { "BDdHOj3W": { - "id": "BDdHOj3W", "type": "simple", + "id": "BDdHOj3W", "question": "The profile drag of a wing section or blade element is proportional to:\n1) the relative velocity of the air.\n2) the square of the relative velocity of the air.\n3) the drag coefficient.\n4) the square root of the drag coefficient.\nWhich of the statements above are correct?", "options": [ { @@ -35041,12 +35041,12 @@ }, { "id": "QW13K4K3AC", - "explanation": "", "learningObjectives": ["081.01.01.05.12"], + "explanation": "", "variants": { "8VkTvcu2": { - "id": "8VkTvcu2", "type": "simple", + "id": "8VkTvcu2", "question": "An aeroplane’s angle of incidence is defined as the angle between the...", "options": [ { @@ -35082,12 +35082,12 @@ }, { "id": "QW1PM1I1OC", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "l1jEz6o0": { - "id": "l1jEz6o0", "type": "simple", + "id": "l1jEz6o0", "question": "Refer to figure. \n The high lift device shown in the figure 2 is a:", "options": [ { @@ -35123,12 +35123,12 @@ }, { "id": "QW2QPUMWNO", - "explanation": "", "learningObjectives": ["081.01.10.02.01"], + "explanation": "", "variants": { "CaMfOM6V": { - "id": "CaMfOM6V", "type": "simple", + "id": "CaMfOM6V", "question": "Speed brakes are devices used on large transport category aircraft:", "options": [ { @@ -35164,12 +35164,12 @@ }, { "id": "QW4COK3PFC", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "xMoUypun": { - "id": "xMoUypun", "type": "simple", + "id": "xMoUypun", "question": "An experimental aircraft has a rectangular wing that is producing a drag value of 867 N, when generating zero lift. Determine the value of drag if the wing area was increased by 10%:", "options": [ { @@ -35205,12 +35205,12 @@ }, { "id": "QWB8YX9GIB", - "explanation": "", "learningObjectives": ["081.01", "081.08"], + "explanation": "", "variants": { "g2rHckP5": { - "id": "g2rHckP5", "type": "simple", + "id": "g2rHckP5", "question": "During a co-ordinated climbing turn to the right the:", "options": [ { @@ -35246,12 +35246,12 @@ }, { "id": "QWD0I7IRIR", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "p2q66FO0": { - "id": "p2q66FO0", "type": "simple", + "id": "p2q66FO0", "question": "If you are flying at 1.4 V~s~ and accelerate to 2.4 V~s~, by how much will the coefficient of lift decrease?", "options": [ { @@ -35287,12 +35287,12 @@ }, { "id": "QWELFNVMNM", - "explanation": "", "learningObjectives": ["081.01.03.03.02"], + "explanation": "", "variants": { "TjCorb5n": { - "id": "TjCorb5n", "type": "simple", + "id": "TjCorb5n", "question": "Refer to the image\nAssuming all bodies have the same cross-sectional area and are in motion, which body will have the highest pressure drag?", "options": [ { @@ -35328,12 +35328,12 @@ }, { "id": "QWGALFYMGG", - "explanation": "", "learningObjectives": ["081.01.05.07.03"], + "explanation": "", "variants": { "sId0hWS8": { - "id": "sId0hWS8", "type": "simple", + "id": "sId0hWS8", "question": "An aircraft is said to have speed stability:", "options": [ { @@ -35369,12 +35369,12 @@ }, { "id": "QWPS6F33DP", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "G39ck8NP": { - "id": "G39ck8NP", "type": "simple", + "id": "G39ck8NP", "question": "An aircraft has a C~L~ value of 1.22 at a speed of 1.1 V~S~. Determine the C~L~ at a speed of 1.8 V~S~:", "options": [ { @@ -35410,12 +35410,12 @@ }, { "id": "QWRKUKWU0H", - "explanation": "", "learningObjectives": ["081.01.04.02.07"], + "explanation": "", "variants": { "T1hzdMsM": { - "id": "T1hzdMsM", "type": "simple", + "id": "T1hzdMsM", "question": "If flaps are deployed at constant IAS in straight and level flight, the magnitude of tip vortices will eventually: (flap span less than wing span)\n \n ", "options": [ { @@ -35451,12 +35451,12 @@ }, { "id": "QWS63ADAEY", - "explanation": "", "learningObjectives": ["081.01.09.01.08"], + "explanation": "", "variants": { "oeZOanCZ": { - "id": "oeZOanCZ", "type": "simple", + "id": "oeZOanCZ", "question": "Assume that an aircraft is performing a series of take-off in different flap configurations. If the flaps are lowered the take-off distance required is _____.", "options": [ { @@ -35492,12 +35492,12 @@ }, { "id": "QWXZDW57PV", - "explanation": "", "learningObjectives": ["081.01.01.02.03"], + "explanation": "", "variants": { "g6nWTRvl": { - "id": "g6nWTRvl", "type": "simple", + "id": "g6nWTRvl", "question": "Consider a subsonic airflow moving steadily through the Venturi Tube with no leaks, as represented in the image.\na, b, c and d identify areas of different speeds. What is the sequence that represents an increasing magnitude of airflow speed?", "options": [ { @@ -35533,12 +35533,12 @@ }, { "id": "QX1CH5Z2XB", - "explanation": "", "learningObjectives": ["081.01.12.02.02"], + "explanation": "", "variants": { "P2koK1xe": { - "id": "P2koK1xe", "type": "simple", + "id": "P2koK1xe", "question": "Flying in icing conditions may result in the stall warning system failing to trigger. This is due to the aeroplane stalling at a lower _____, because of premature boundary layer separation.", "options": [ { @@ -35574,12 +35574,12 @@ }, { "id": "QX2M9ACQ2C", - "explanation": "", "learningObjectives": ["081.01.01.01.01"], + "explanation": "", "variants": { "EGLxeIxF": { - "id": "EGLxeIxF", "type": "simple", + "id": "EGLxeIxF", "question": "The SI unit for force is:", "options": [ { @@ -35615,12 +35615,12 @@ }, { "id": "QXVBC7JZ6B", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "Q35eNa1b": { - "id": "Q35eNa1b", "type": "simple", + "id": "Q35eNa1b", "question": "When trailing edge flaps are extended whilst maintaining straight and level flight at constant IAS:", "options": [ { @@ -35656,12 +35656,12 @@ }, { "id": "QX4J4HZ7MT", - "explanation": "", "learningObjectives": ["081.01.01.01.16"], + "explanation": "", "variants": { "TEsqj0Mh": { - "id": "TEsqj0Mh", "type": "simple", + "id": "TEsqj0Mh", "question": "The equation of continuity states that for a low subsonic flow and assuming that the air is incompressible, the constant mass flow in a stream tube, is dependent on:", "options": [ { @@ -35697,12 +35697,12 @@ }, { "id": "QX4KE344XK", - "explanation": "", "learningObjectives": ["081.01.09.02.03"], + "explanation": "", "variants": { "YYE9Kx98": { - "id": "YYE9Kx98", "type": "simple", + "id": "YYE9Kx98", "question": "The extension of trailing edge flaps moves the CP:", "options": [ { @@ -35738,12 +35738,12 @@ }, { "id": "QXCVT1DOR1", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "ojlUd9Ve": { - "id": "ojlUd9Ve", "type": "simple", + "id": "ojlUd9Ve", "question": "Refer to figure 081-45.\nIn the annex attached, which of the following devices will increase your critical angle of attack? ", "options": [ { @@ -35782,12 +35782,12 @@ }, { "id": "QXJB5C2GVY", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "Ah3nD0an": { - "id": "Ah3nD0an", "type": "simple", + "id": "Ah3nD0an", "question": "The lift force, acting on an aerofoil:", "options": [ { @@ -35823,12 +35823,12 @@ }, { "id": "QXLOJYC35K", - "explanation": "", "learningObjectives": ["081.01.10.02.01"], + "explanation": "", "variants": { "0UB3uIIR": { - "id": "0UB3uIIR", "type": "simple", + "id": "0UB3uIIR", "question": "Many aeroplanes are equipped with speed brakes. Speed brakes are usually made up of one or several panels:", "options": [ { @@ -35864,12 +35864,12 @@ }, { "id": "QXPCKMOGY6", - "explanation": "", "learningObjectives": ["081.01.04.03.07"], + "explanation": "", "variants": { "7e0tkRkq": { - "id": "7e0tkRkq", "type": "simple", + "id": "7e0tkRkq", "question": "What is the effect of decreased upwash of the wing?", "options": [ { @@ -35905,12 +35905,12 @@ }, { "id": "QXPLH9LKOD", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "TJHOdxtV": { - "id": "TJHOdxtV", "type": "simple", + "id": "TJHOdxtV", "question": "The aerofoil polar is:", "options": [ { @@ -35946,12 +35946,12 @@ }, { "id": "QXRWRW5UN2", - "explanation": "", "learningObjectives": ["081.01.03.02.04"], + "explanation": "", "variants": { "vBj4GqYW": { - "id": "vBj4GqYW", "type": "simple", + "id": "vBj4GqYW", "question": "In straight and level flight at a speed of 1.8Vs, the Lift Coefficient expressed as a percentage of C~LMAX~ would be:", "options": [ { @@ -35987,12 +35987,12 @@ }, { "id": "QXSV6ZGU1O", - "explanation": "", "learningObjectives": ["081.01.01.05.03"], + "explanation": "", "variants": { "afsy33jS": { - "id": "afsy33jS", "type": "simple", + "id": "afsy33jS", "question": "Taper ratio is the ratio of:", "options": [ { @@ -36028,12 +36028,12 @@ }, { "id": "QXY8JCQD2T", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "POJ4UcMj": { - "id": "POJ4UcMj", "type": "simple", + "id": "POJ4UcMj", "question": "Refer to figure. \n From the following, select the graph or graphs that represent an aerofoil with negative camber.", "options": [ { @@ -36069,12 +36069,12 @@ }, { "id": "QY08W4S2SI", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "pwxeiyXH": { - "id": "pwxeiyXH", "type": "simple", + "id": "pwxeiyXH", "question": "An aerofoil with reduced camber compared to one with increased camber at high subsonic speed, at the same level and configuration will", "options": [ { @@ -36110,12 +36110,12 @@ }, { "id": "QY3KB1Z3X4", - "explanation": "", "learningObjectives": ["081.01.02.01.02"], + "explanation": "", "variants": { "v1zOFdrf": { - "id": "v1zOFdrf", "type": "simple", + "id": "v1zOFdrf", "question": "A streamline flow approaches an aerofoil and pauses at the stagnation point. At this point, the static pressure:", "options": [ { @@ -36151,12 +36151,12 @@ }, { "id": "QY5ZZK7PS8", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "StRJViYX": { - "id": "StRJViYX", "type": "simple", + "id": "StRJViYX", "question": "Given the following aeroplane configurations \n1.Clean wing\n2.Slats only extended\n3.Flaps only extended\n Place these configurations in order of increasing critical angle of attack", "options": [ { @@ -36192,12 +36192,12 @@ }, { "id": "QYBB626991", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "eFsHAXi9": { - "id": "eFsHAXi9", "type": "simple", + "id": "eFsHAXi9", "question": "If the lift generated by a given wing is 1 000 kN, what will be the lift if the wing area is doubled?", "options": [ { @@ -36233,12 +36233,12 @@ }, { "id": "QYBTD07QXA", - "explanation": "", "learningObjectives": ["081.01.01.04.04"], + "explanation": "", "variants": { "LqbcigQI": { - "id": "LqbcigQI", "type": "simple", + "id": "LqbcigQI", "question": "The thickness to chord ratio of an aerofoil is...", "options": [ { @@ -36274,12 +36274,12 @@ }, { "id": "QYC3MEJZVU", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "iBzEMaKo": { - "id": "iBzEMaKo", "type": "simple", + "id": "iBzEMaKo", "question": "By lowering the trailing edge flaps...", "options": [ { @@ -36315,12 +36315,12 @@ }, { "id": "QYHY6K3O3N", - "explanation": "", "learningObjectives": ["081.01.01.01.09"], + "explanation": "", "variants": { "W7v5IHsV": { - "id": "W7v5IHsV", "type": "simple", + "id": "W7v5IHsV", "question": "The unit of measurement of pressure is:", "options": [ { @@ -36356,12 +36356,12 @@ }, { "id": "QYJ5MLNHFO", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "ObrVBEdO": { - "id": "ObrVBEdO", "type": "simple", + "id": "ObrVBEdO", "question": "An aeroplane has the following flap positions 0°, 15°, 30°, 45°; slats can also be selected. Generally speaking, which selection provides the highest positive contribution to the C~LMAX~?", "options": [ { @@ -36397,12 +36397,12 @@ }, { "id": "QYN07ISNW3", - "explanation": "", "learningObjectives": ["081.01.12.01.03"], + "explanation": "", "variants": { "Zxf1QLDK": { - "id": "Zxf1QLDK", "type": "simple", + "id": "Zxf1QLDK", "question": "It is a cold day with visible moisture. You do not de-ice and there is no anti-icing available. How will this affect the aircraft performance?", "options": [ { @@ -36438,12 +36438,12 @@ }, { "id": "QYOARPHCJL", - "explanation": "", "learningObjectives": ["081.01.03.02.04"], + "explanation": "", "variants": { "CxMHA4pa": { - "id": "CxMHA4pa", "type": "simple", + "id": "CxMHA4pa", "question": "An aeroplane is in level flight at 146 kts with a Lift coefficient (C~L~) of 0.91. If the 1g stall speed is 109 kts, what is the value of C~LMAX~?", "options": [ { @@ -36479,12 +36479,12 @@ }, { "id": "QYQZFSGADW", - "explanation": "", "learningObjectives": ["081.01.02.01.02"], + "explanation": "", "variants": { "ry8iVNTR": { - "id": "ry8iVNTR", "type": "simple", + "id": "ry8iVNTR", "question": "Which of these statements about a steady subsonic flow are correct or incorrect?\n\n1. The static pressure does not change as the streamlines diverge.\n\n2. The velocity decreases as the streamlines diverge.", "options": [ { @@ -36520,12 +36520,12 @@ }, { "id": "QYS44JPHHS", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "gpWH4c5A": { - "id": "gpWH4c5A", "type": "simple", + "id": "gpWH4c5A", "question": "Whilst maintaining straight and level flight with a lift coefficient C~L~ = 1 what will be the new approximate value of C~L~ after the speed is increased by 30%?", "options": [ { @@ -36561,12 +36561,12 @@ }, { "id": "QYTEW1EAVC", - "explanation": "", "learningObjectives": ["081.01.01.01.11"], + "explanation": "", "variants": { "w2tYdlfb": { - "id": "w2tYdlfb", "type": "simple", + "id": "w2tYdlfb", "question": "Consider the following expression: \"In a streamlined flow of fluid, the sum of all energies is a constant\". It derives from:", "options": [ { @@ -36602,12 +36602,12 @@ }, { "id": "QYUWBMYFY7", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "dQo5bVaP": { - "id": "dQo5bVaP", "type": "simple", + "id": "dQo5bVaP", "question": "Assuming zero thrust, the point on the image corresponding to the value for minimum sink rate is", "options": [ { @@ -36640,8 +36640,8 @@ "explanation": "" }, "QJhDG8ZW": { - "id": "QJhDG8ZW", "type": "simple", + "id": "QJhDG8ZW", "question": "Assuming zero thrust, the point on the image corresponding to the value for minimum sink rate is", "options": [ { @@ -36677,12 +36677,12 @@ }, { "id": "QYV79C1NQP", - "explanation": "", "learningObjectives": ["081.01.03.02.04"], + "explanation": "", "variants": { "8wKH3qsH": { - "id": "8wKH3qsH", "type": "simple", + "id": "8wKH3qsH", "question": "Consider the ‘’CL vs angle of attack’’ graph of a non-symmetrical airfoil with the X axis representing angle of attack, and the Y axis representing CL. \n The angle of attack at which the aerofoil achieves CL~MAX~ can be found on the graph...", "options": [ { @@ -36718,12 +36718,12 @@ }, { "id": "QYV93GNZO9", - "explanation": "", "learningObjectives": ["081.01.09.01.07"], + "explanation": "", "variants": { "qPPTTraF": { - "id": "qPPTTraF", "type": "simple", + "id": "qPPTTraF", "question": "Refer to figure 081-51.\nAfter take off a pilot retracts the trailing edge flaps, but the right flaps become stuck in the down position. What control inputs must the pilot make to counter this flap asymmetry?", "options": [ { @@ -36762,12 +36762,12 @@ }, { "id": "QYYLI2KV8L", - "explanation": "", "learningObjectives": ["081.01.01.04.03"], + "explanation": "", "variants": { "mU799Dr8": { - "id": "mU799Dr8", "type": "simple", + "id": "mU799Dr8", "question": "Refer to figure. \n What is the correct combination of letters identifying the airfoils with the corresponding numbers from the C~D~ graphic?", "options": [ { @@ -36803,12 +36803,12 @@ }, { "id": "QYZUDL3WA6", - "explanation": "", "learningObjectives": ["081.01.09.01.09"], + "explanation": "", "variants": { "yneaaPqg": { - "id": "yneaaPqg", "type": "simple", + "id": "yneaaPqg", "question": "After engine start, the pilots forget to lower the flap setting for departure. What is the consequence of this?", "options": [ { @@ -36844,12 +36844,12 @@ }, { "id": "QZ3GUI5SED", - "explanation": "", "learningObjectives": ["081.01.04.03.01"], + "explanation": "", "variants": { "PMUTWHCh": { - "id": "PMUTWHCh", "type": "simple", + "id": "PMUTWHCh", "question": "Which of the following would cause a reduction in interference drag?", "options": [ { @@ -36885,12 +36885,12 @@ }, { "id": "QZ423LFBOI", - "explanation": "", "learningObjectives": ["081.01.09.02.03"], + "explanation": "", "variants": { "zHkDsQKw": { - "id": "zHkDsQKw", "type": "simple", + "id": "zHkDsQKw", "question": "Extending flaps will I. _______the wing’s effective camber and, consequently, II. ______ the stall speed.", "options": [ { @@ -36926,12 +36926,12 @@ }, { "id": "QZ83NAZRJH", - "explanation": "", "learningObjectives": ["081.01.02.09.02"], + "explanation": "", "variants": { "NUsiEpk5": { - "id": "NUsiEpk5", "type": "simple", + "id": "NUsiEpk5", "question": "The lift coefficient C~L~ versus angle of attack curve of a symmetrical aerofoil section intersects the vertical axis of the graph, where the...", "options": [ { @@ -36967,12 +36967,12 @@ }, { "id": "QZB4SFDBHL", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "8JwpwyJu": { - "id": "8JwpwyJu", "type": "simple", + "id": "8JwpwyJu", "question": "In straight and level flight at a speed of 1.5 V~S~, the lift coefficient, expressed as a percentage of its maximum CL~MAX~, would be:", "options": [ { @@ -37005,8 +37005,8 @@ "explanation": "" }, "gLRUslvp": { - "id": "gLRUslvp", "type": "simple", + "id": "gLRUslvp", "question": "In straight and level flight at a speed of 1.8 V~S~, the lift coefficient, expressed as a percentage of its maximum CL~MAX~, would be:", "options": [ { @@ -37039,8 +37039,8 @@ "explanation": "" }, "TzLqYvy8": { - "id": "TzLqYvy8", "type": "simple", + "id": "TzLqYvy8", "question": "In straight and level flight at a speed of 1.6 V~S~, the lift coefficient, expressed as a percentage of its maximum CL~MAX~, would be:", "options": [ { @@ -37073,8 +37073,8 @@ "explanation": "" }, "s45lgljC": { - "id": "s45lgljC", "type": "simple", + "id": "s45lgljC", "question": "In straight and level flight at a speed of 1.7 V~S~, the lift coefficient, expressed as a percentage of its maximum CL~MAX~, would be:", "options": [ { @@ -37107,8 +37107,8 @@ "explanation": "" }, "rR7BHiX5": { - "id": "rR7BHiX5", "type": "simple", + "id": "rR7BHiX5", "question": "In straight and level flight at a speed of 1.9 V~S~, the lift coefficient, expressed as a percentage of its maximum CL~MAX~, would be:", "options": [ { @@ -37141,8 +37141,8 @@ "explanation": "" }, "R0Xl1gQo": { - "id": "R0Xl1gQo", "type": "simple", + "id": "R0Xl1gQo", "question": "In straight and level flight at a speed of 1.2 V~S~, the lift coefficient, expressed as a percentage of its maximum CL~MAX~, would be:", "options": [ { @@ -37175,8 +37175,8 @@ "explanation": "" }, "GGL1xJmU": { - "id": "GGL1xJmU", "type": "simple", + "id": "GGL1xJmU", "question": "In straight and level flight at a speed of 1.3 V~S~, the lift coefficient, expressed as a percentage of its maximum CL~MAX~, would be:", "options": [ { @@ -37209,8 +37209,8 @@ "explanation": "" }, "W8aov8TT": { - "id": "W8aov8TT", "type": "simple", + "id": "W8aov8TT", "question": "In straight and level flight at a speed of 1.4 V~S~, the lift coefficient, expressed as a percentage of its maximum CL~MAX~, would be:", "options": [ { @@ -37243,8 +37243,8 @@ "explanation": "" }, "5RVgwKyM": { - "id": "5RVgwKyM", "type": "simple", + "id": "5RVgwKyM", "question": "In straight and level flight at a speed of 1.1 V~S~, the lift coefficient, expressed as a percentage of its maximum CL~MAX~, would be:", "options": [ { @@ -37280,12 +37280,12 @@ }, { "id": "QZJRIZDCAT", - "explanation": "", "learningObjectives": ["081.01.05.07.01"], + "explanation": "", "variants": { "SwtMiu3w": { - "id": "SwtMiu3w", "type": "simple", + "id": "SwtMiu3w", "question": "If an aeroplane is at a higher mass than anticipated, for a given airspeed the angle of attack will", "options": [ { @@ -37321,12 +37321,12 @@ }, { "id": "QZSG3LP1EE", - "explanation": "", "learningObjectives": ["081.01.09.02.06"], + "explanation": "", "variants": { "Aa3t1xn9": { - "id": "Aa3t1xn9", "type": "simple", + "id": "Aa3t1xn9", "question": "C~L~ varies with:", "options": [ { @@ -37362,12 +37362,12 @@ }, { "id": "QZZVKAWDTB", - "explanation": "", "learningObjectives": ["081.01.04.03.12"], + "explanation": "", "variants": { "UISBB6F8": { - "id": "UISBB6F8", "type": "simple", + "id": "UISBB6F8", "question": "Considering the polar curve of a subsonic aerofoil, the maximum lift-to-drag ratio is determined by..", "options": [ { @@ -37403,12 +37403,12 @@ }, { "id": "QZZVR013N9", - "explanation": "", "learningObjectives": ["081.01.03.02.01"], + "explanation": "", "variants": { "Dys7ZmS4": { - "id": "Dys7ZmS4", "type": "simple", + "id": "Dys7ZmS4", "question": "Which of the following variables are required to calculate lift from the lift formula?", "options": [ { @@ -37444,12 +37444,31 @@ }, { "id": "QYFPA3CY4E", - "explanation": "# TLDR\n\nIn a venturi...\n\n- **Total Pressure remains constant**, and...\n- **Mass flow remains constant** (for incompressible flows). Therefore...\n- **Speed increases at the throat**, therefore...\n- **Dynamic pressure increases at the throat**, therefore...\n- **Static pressure decreases at the throat**\n\n# Long Explanation\n\nThe Bernoulli's principle states that in a fluid flow, an increase in velocity\nresults in a decrease in pressure, and vice versa. This principle is commonly\nused to explain the behavior of fluids in motion, such as in the case of an\nairplane wing or a Venturi tube.\nThe formula for total pressure in a fluid flow is the sum of dynamic pressure\nand static pressure. Dynamic pressure is the pressure due to the motion of the\nfluid, while static pressure is the pressure of the fluid when it is at rest.\nThe total pressure is important to consider in fluid flow calculations, as it\nis a measure of the energy contained in the fluid.\n\nWhen a fluid flows through a Venturi tube, the constriction in the tube causes\nthe velocity of the fluid to increase, according to the Bernoulli's principle.\nThis increase in velocity results in a decrease in static pressure in the\nthroat of the tube. However, the total pressure of the fluid remains constant\nthroughout the tube. Therefore, as the velocity increases, the static\npressure decreases to maintain the constant total pressure. This phenomenon\nis used in many applications, such as in carburetors for gasoline engines\nor in fluid metering devices.", "learningObjectives": ["081.01.01.01.13"], + "explanation": "# TLDR\n\nIn a venturi...\n\n- **Total Pressure remains constant**, and...\n- **Mass flow remains constant** (for incompressible flows). Therefore...\n- **Speed increases at the throat**, therefore...\n- **Dynamic pressure increases at the throat**, therefore...\n- **Static pressure decreases at the throat**\n\n# Long Explanation\n\nThe Bernoulli's principle states that in a fluid flow, an increase in velocity\nresults in a decrease in pressure, and vice versa. This principle is commonly\nused to explain the behavior of fluids in motion, such as in the case of an\nairplane wing or a Venturi tube.\nThe formula for total pressure in a fluid flow is the sum of dynamic pressure\nand static pressure. Dynamic pressure is the pressure due to the motion of the\nfluid, while static pressure is the pressure of the fluid when it is at rest.\nThe total pressure is important to consider in fluid flow calculations, as it\nis a measure of the energy contained in the fluid.\n\nWhen a fluid flows through a Venturi tube, the constriction in the tube causes\nthe velocity of the fluid to increase, according to the Bernoulli's principle.\nThis increase in velocity results in a decrease in static pressure in the\nthroat of the tube. However, the total pressure of the fluid remains constant\nthroughout the tube. Therefore, as the velocity increases, the static\npressure decreases to maintain the constant total pressure. This phenomenon\nis used in many applications, such as in carburetors for gasoline engines\nor in fluid metering devices.", "variants": { "QYFPA3CY4F": { "type": "one-two", "id": "QYFPA3CY4F", + "question": "Considering subsonic incompressible airflow through a Venturi, which statement is correct?", + "firstCorrectStatements": [ + "The dynamic pressure in the throat is higher than in the undisturbed airflow." + ], + "firstIncorrectStatements": [ + "The dynamic pressure in the throat is lower than in the undisturbed airflow.", + "The dynamic pressure in the throat is same than in the undisturbed airflow." + ], + "secondCorrectStatements": [ + "The static pressure in the throat is lower than in the undisturbed airflow.", + "The total pressure in the throat is the same as in the undisturbed airflow." + ], + "secondIncorrectStatements": [ + "The static pressure in the throat is higher than in the undisturbed airflow.", + "The static pressure in the throat is the same than in the undisturbed airflow.", + "The total pressure in the throat is higher than in the undisturbed airflow.", + "The total pressure in the throat is lower than in the undisturbed airflow." + ], + "annexes": [], "externalIds": [ "ATPLQ-812330", "ATPLQ-816383", @@ -37573,37 +37592,18 @@ "AVEXAM-9113", "ATPLGS-625823" ], - "annexes": [], - "question": "Considering subsonic incompressible airflow through a Venturi, which statement is correct?", - "firstCorrectStatements": [ - "The dynamic pressure in the throat is higher than in the undisturbed airflow." - ], - "firstIncorrectStatements": [ - "The dynamic pressure in the throat is lower than in the undisturbed airflow.", - "The dynamic pressure in the throat is same than in the undisturbed airflow." - ], - "secondCorrectStatements": [ - "The static pressure in the throat is lower than in the undisturbed airflow.", - "The total pressure in the throat is the same as in the undisturbed airflow." - ], - "secondIncorrectStatements": [ - "The static pressure in the throat is higher than in the undisturbed airflow.", - "The static pressure in the throat is the same than in the undisturbed airflow.", - "The total pressure in the throat is higher than in the undisturbed airflow.", - "The total pressure in the throat is lower than in the undisturbed airflow." - ], "explanation": "" } } }, { "id": "QYGRSBZN3U", - "explanation": "", "learningObjectives": ["081.01", "081.02"], + "explanation": "", "variants": { "Gp0fmo6X": { - "id": "Gp0fmo6X", "type": "simple", + "id": "Gp0fmo6X", "question": "Considering streamlines over an aerofoil, which of the following is correct:", "options": [ { @@ -37639,12 +37639,12 @@ }, { "id": "QDNJ4PN2RT", - "explanation": "", "learningObjectives": ["081.01", "081.02"], + "explanation": "", "variants": { "JTAxLABf": { - "id": "JTAxLABf", "type": "simple", + "id": "JTAxLABf", "question": "The boundary layer will separate from the aerofoil immediately..", "options": [ { @@ -37680,12 +37680,12 @@ }, { "id": "QCYE792UP2", - "explanation": "", "learningObjectives": ["081.01", "081.03"], + "explanation": "", "variants": { "Vs0O7s69": { - "id": "Vs0O7s69", "type": "simple", + "id": "Vs0O7s69", "question": "If the aspect ratio of a wing increases whilst all other relevant factors remain constant, the critical angle of attack will:", "options": [ { @@ -37723,8 +37723,8 @@ "explanation": "" }, "CuY9URpu": { - "id": "CuY9URpu", "type": "simple", + "id": "CuY9URpu", "question": "If the aspect ratio of a wing increases whilst all other relevant factors remain constant, the stall angle of attack will:", "options": [ { @@ -37760,12 +37760,12 @@ }, { "id": "Q2Y377AJF7", - "explanation": "", "learningObjectives": ["081.01", "081.03"], + "explanation": "", "variants": { "NrmgnJ0z": { - "id": "NrmgnJ0z", "type": "simple", + "id": "NrmgnJ0z", "question": "In which phase of the take-off is the aerodynamic effect of ice located on the wing leading edge most critical?", "options": [ { @@ -37798,8 +37798,8 @@ "explanation": "" }, "CBRpGNoT": { - "id": "CBRpGNoT", "type": "simple", + "id": "CBRpGNoT", "question": "In which phase of the take-off is the aerodynamic effect of ice located on the wing leading edge most critical?", "options": [ { @@ -37835,12 +37835,12 @@ }, { "id": "Q9O8IRA57X", - "explanation": "", "learningObjectives": ["081.01", "081.03"], + "explanation": "", "variants": { "67Wqt9xm": { - "id": "67Wqt9xm", "type": "simple", + "id": "67Wqt9xm", "question": "Load factor is:", "options": [ { @@ -37881,12 +37881,12 @@ }, { "id": "QVLMTYXMSY", - "explanation": "", "learningObjectives": ["081.01", "081.03"], + "explanation": "", "variants": { "BYEQf873": { - "id": "BYEQf873", "type": "simple", + "id": "BYEQf873", "question": "The boundary layer of a wing is:", "options": [ { @@ -37927,12 +37927,12 @@ }, { "id": "Q2Q8Q6FDQE", - "explanation": "", "learningObjectives": ["081.01", "081.03"], + "explanation": "", "variants": { "PCKzfhuT": { - "id": "PCKzfhuT", "type": "simple", + "id": "PCKzfhuT", "question": "What will happen to the stall speed, stalling Angle Of Attack (AOA) and controllability of an aircraft in flight due to icing?", "options": [ { @@ -37968,12 +37968,12 @@ }, { "id": "QNOK75QOAR", - "explanation": "", "learningObjectives": ["081.01", "081.03"], + "explanation": "", "variants": { "kW9U4L4d": { - "id": "kW9U4L4d", "type": "simple", + "id": "kW9U4L4d", "question": "What is the percentage increase in stall speed in a 45° bank turn?", "options": [ { @@ -38006,8 +38006,8 @@ "explanation": "" }, "8qRsejU4": { - "id": "8qRsejU4", "type": "simple", + "id": "8qRsejU4", "question": "What is the percentage increase in stall speed in a 45° bank turn?", "options": [ { @@ -38043,12 +38043,12 @@ }, { "id": "QWNOI54GXB", - "explanation": "", "learningObjectives": ["081.01", "081.04"], + "explanation": "", "variants": { "ZxEwYJPV": { - "id": "ZxEwYJPV", "type": "simple", + "id": "ZxEwYJPV", "question": "Why do stick forces per g decrease at high altitude?", "options": [ { @@ -38084,12 +38084,12 @@ }, { "id": "Q7NHSPH4XL", - "explanation": "", "learningObjectives": ["081.01", "081.05"], + "explanation": "", "variants": { "vzZCJclK": { - "id": "vzZCJclK", "type": "simple", + "id": "vzZCJclK", "question": "Which component of drag increases most when an aileron is deflected upwards?", "options": [ { @@ -38130,12 +38130,12 @@ }, { "id": "QV1HSK45JM", - "explanation": "", "learningObjectives": ["081.01", "081.06"], + "explanation": "", "variants": { "7inlqOo8": { - "id": "7inlqOo8", "type": "simple", + "id": "7inlqOo8", "question": "Where does ice form on on a wing in straight and level flight?", "options": [ { @@ -38171,12 +38171,12 @@ }, { "id": "QN427T4AET", - "explanation": "", "learningObjectives": ["081.01", "081.06"], + "explanation": "", "variants": { "u3ykZN3r": { - "id": "u3ykZN3r", "type": "simple", + "id": "u3ykZN3r", "question": "Under CS 23 and CS 25, which of the following statements is correct?", "options": [ { @@ -38212,12 +38212,12 @@ }, { "id": "Q1VW5Q2U52", - "explanation": "", "learningObjectives": ["081.01", "081.07"], + "explanation": "", "variants": { "IqRvJVYy": { - "id": "IqRvJVYy", "type": "simple", + "id": "IqRvJVYy", "question": "When a propeller is feathered:", "options": [ { @@ -38250,8 +38250,8 @@ "explanation": "" }, "CFyasMS7": { - "id": "CFyasMS7", "type": "simple", + "id": "CFyasMS7", "question": "When a propeller is feathered:", "options": [ { @@ -38287,12 +38287,12 @@ }, { "id": "QCWY1B6XUO", - "explanation": "", "learningObjectives": ["081.01", "081.08"], + "explanation": "", "variants": { "Tb8bn4Ej": { - "id": "Tb8bn4Ej", "type": "simple", + "id": "Tb8bn4Ej", "question": "An aeroplane is in straight and level flight, with constant IAS. If the flaps are retracted and action is taken to maintain the aeroplane in straight and level flight at constant IAS, the lift coefficient will..", "options": [ { @@ -38325,8 +38325,8 @@ "explanation": "" }, "LYvyF4FY": { - "id": "LYvyF4FY", "type": "simple", + "id": "LYvyF4FY", "question": "An aeroplane is in straight and level flight, with constant IAS. If the flaps are retracted and action is taken to maintain the aeroplane in straight and level flight at constant IAS, the lift coefficient will...", "options": [ { @@ -38362,12 +38362,12 @@ }, { "id": "QM3P8B9MLM", - "explanation": "", "learningObjectives": ["081.01", "081.08"], + "explanation": "", "variants": { "T9996TOV": { - "id": "T9996TOV", "type": "simple", + "id": "T9996TOV", "question": "High lift devices will", "options": [ { @@ -38400,8 +38400,8 @@ "explanation": "" }, "0Oxc0zLN": { - "id": "0Oxc0zLN", "type": "simple", + "id": "0Oxc0zLN", "question": "High lift devices will", "options": [ { @@ -38437,12 +38437,12 @@ }, { "id": "Q01E5B2P6W", - "explanation": "", "learningObjectives": ["081.01.04.03.04"], + "explanation": "", "variants": { "rPzEPMW3": { - "id": "rPzEPMW3", "type": "simple", + "id": "rPzEPMW3", "question": "If IAS remains constant, the effect of decreasing aeroplane mass is that M~CRIT~:", "options": [ { @@ -38478,12 +38478,12 @@ }, { "id": "Q0UC93BIGD", - "explanation": "", "learningObjectives": ["081.01.04.02.03"], + "explanation": "", "variants": { "NlpvpRyw": { - "id": "NlpvpRyw", "type": "simple", + "id": "NlpvpRyw", "question": "Which of these statements about \"tuck under\" are correct or incorrect?\n\n1. A contributing factor to \"tuck under\" is an aft movement of the centre of pressure of the wing.\n\n2. A contributing factor to \"tuck under\" is an increase in the downwash angle at the location of the horizontal stabiliser.", "options": [ { @@ -38527,12 +38527,12 @@ }, { "id": "Q145HSG0T2", - "explanation": "", "learningObjectives": ["081.01.09.03.01"], + "explanation": "", "variants": { "Emn8BhOb": { - "id": "Emn8BhOb", "type": "simple", + "id": "Emn8BhOb", "question": "Vortex generators on the upper side of the wing surface will", "options": [ { @@ -38568,12 +38568,12 @@ }, { "id": "QQPGWKCNLQ", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "gP4sHT5X": { - "id": "gP4sHT5X", "type": "simple", + "id": "gP4sHT5X", "question": "What happens to the lift to drag ratio in the transonic regime?", "options": [ { @@ -38609,12 +38609,12 @@ }, { "id": "Q22T0ICX5G", - "explanation": "", "learningObjectives": ["081.01.10.02.05"], + "explanation": "", "variants": { "eJJH2Yvr": { - "id": "eJJH2Yvr", "type": "simple", + "id": "eJJH2Yvr", "question": "The rate and depth of breathing is primarily controlled by the", "options": [ { @@ -38650,12 +38650,12 @@ }, { "id": "Q28IGHB4Y2", - "explanation": "", "learningObjectives": ["081.01.04.03.05"], + "explanation": "", "variants": { "yyv12MSa": { - "id": "yyv12MSa", "type": "simple", + "id": "yyv12MSa", "question": "To reduce friction drag, some aeroplanes are equipped with modified wing designs to:", "options": [ { @@ -38691,12 +38691,12 @@ }, { "id": "Q31MBA4IYI", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "0ugYmMI6": { - "id": "0ugYmMI6", "type": "simple", + "id": "0ugYmMI6", "question": "Which of the following aerofoils and angles of attack will produce the lowest M~CRIT~ values?", "options": [ { @@ -38732,12 +38732,12 @@ }, { "id": "Q3DVHT0O9Q", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "ENP0djbL": { - "id": "ENP0djbL", "type": "simple", + "id": "ENP0djbL", "question": "Using a thin section wing....(1).... the onset of the transonic drag rise and....(2)....the peak value of CD", "options": [ { @@ -38773,12 +38773,12 @@ }, { "id": "QER4I6EDCB", - "explanation": "", "learningObjectives": ["081.01.04.03.04"], + "explanation": "", "variants": { "lrvS6Wju": { - "id": "lrvS6Wju", "type": "simple", + "id": "lrvS6Wju", "question": "Whilst flying at a constant IAS and at n = 1, as the aeroplane mass decreases, the value of Mcrit:", "options": [ { @@ -38820,12 +38820,12 @@ }, { "id": "Q3PEP2N5XF", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "VqWgCKBj": { - "id": "VqWgCKBj", "type": "simple", + "id": "VqWgCKBj", "question": "When the speed over an aerofoil section increases from subsonic to supersonic, its aerodynamic centre:", "options": [ { @@ -38866,12 +38866,12 @@ }, { "id": "Q3Z4EDPOSC", - "explanation": "", "learningObjectives": ["081.01.04.03.02"], + "explanation": "", "variants": { "zPNP3I20": { - "id": "zPNP3I20", "type": "simple", + "id": "zPNP3I20", "question": "In the transonic region, the coefficient of drag:", "options": [ { @@ -38907,12 +38907,12 @@ }, { "id": "Q54TP39FNO", - "explanation": "", "learningObjectives": ["081.01.01.03.05"], + "explanation": "", "variants": { "YPRVqKv0": { - "id": "YPRVqKv0", "type": "simple", + "id": "YPRVqKv0", "question": "In the transonic speed range the aeroplane characteristics are strongly determined by the:", "options": [ { @@ -38948,12 +38948,12 @@ }, { "id": "Q5JQJ41V3L", - "explanation": "", "learningObjectives": ["081.01.01.05.10"], + "explanation": "", "variants": { "XXW6LpK0": { - "id": "XXW6LpK0", "type": "simple", + "id": "XXW6LpK0", "question": "The effect of increasing angle of sweep is", "options": [ { @@ -38994,12 +38994,12 @@ }, { "id": "Q5YWJGKCQG", - "explanation": "", "learningObjectives": ["081.01.09.02.03"], + "explanation": "", "variants": { "VzDSsh0i": { - "id": "VzDSsh0i", "type": "simple", + "id": "VzDSsh0i", "question": "What type of wing has the least effective trailing edge flaps?", "options": [ { @@ -39035,12 +39035,12 @@ }, { "id": "Q63M0VVEPA", - "explanation": "", "learningObjectives": ["081.01.01.01.15"], + "explanation": "", "variants": { "FTcOgFeN": { - "id": "FTcOgFeN", "type": "simple", + "id": "FTcOgFeN", "question": "The Mach number of an airflow is determined by:\n1) the airspeed.\n2) the air density.\n3) the air pressure.\n4) the air temperature.\nWhich answer contains all correct items?", "options": [ { @@ -39076,12 +39076,12 @@ }, { "id": "QRZOZRAPD8", - "explanation": "", "learningObjectives": ["081.01.01.01.04"], + "explanation": "", "variants": { "a4AUxSil": { - "id": "a4AUxSil", "type": "simple", + "id": "a4AUxSil", "question": "When the air is passing through a shock wave the density will:", "options": [ { @@ -39122,12 +39122,12 @@ }, { "id": "QUNTMXOR02", - "explanation": "", "learningObjectives": ["081.01.01.04.09"], + "explanation": "", "variants": { "Ll7KuQq8": { - "id": "Ll7KuQq8", "type": "simple", + "id": "Ll7KuQq8", "question": "In comparison to a conventional aerofoil section, typical shape characteristics of a supercritical aerofoil section are:", "options": [ { @@ -39168,12 +39168,12 @@ }, { "id": "Q790HZXO51", - "explanation": "", "learningObjectives": ["081.01.01.05.10"], + "explanation": "", "variants": { "PuoMrrS6": { - "id": "PuoMrrS6", "type": "simple", + "id": "PuoMrrS6", "question": "Which of the following items are needed to correctly complete the statement? \nThe characteristics of wing sweep include \n1 a decreased tendency to tip stall\n2 increased take-off and landing distances\n3 a higher stall speed\n4 an increased effectiveness of trailing edge control surfaces\n5 a decreased effectiveness of high lift devices.", "options": [ { @@ -39209,12 +39209,12 @@ }, { "id": "QQIEMEYU3B", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "3XiB7rlO": { - "id": "3XiB7rlO", "type": "simple", + "id": "3XiB7rlO", "question": "Which of the following wing designs would have the least effective high lift devices (airspeed and all other factors being constant)?", "options": [ { @@ -39250,12 +39250,12 @@ }, { "id": "Q7S8R4K63I", - "explanation": "", "learningObjectives": ["081.01.04.03.07"], + "explanation": "", "variants": { "HPE2lMI5": { - "id": "HPE2lMI5", "type": "simple", + "id": "HPE2lMI5", "question": "Behind a normal shock wave, the downwash is greatly reduced. In turn, this causes...", "options": [ { @@ -39291,12 +39291,12 @@ }, { "id": "Q87503Q78G", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "dVH1r1kq": { - "id": "dVH1r1kq", "type": "simple", + "id": "dVH1r1kq", "question": "How does the coefficient of lift change in the transonic region?", "options": [ { @@ -39332,12 +39332,12 @@ }, { "id": "Q8A7H9GQRC", - "explanation": "", "learningObjectives": ["081.01.09.03.01"], + "explanation": "", "variants": { "pc711miE": { - "id": "pc711miE", "type": "simple", + "id": "pc711miE", "question": "Vortex generators mounted on the upper wing surface will", "options": [ { @@ -39373,12 +39373,12 @@ }, { "id": "QD5F0GFAHL", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "t9iqkb9O": { - "id": "t9iqkb9O", "type": "simple", + "id": "t9iqkb9O", "question": "The position of the centre of pressure on an aerofoil of an aeroplane cruising at supersonic speed when compared with that at subsonic speed is:", "options": [ { @@ -39414,12 +39414,12 @@ }, { "id": "QGWCOWIDTS", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "jL2ZME3Q": { - "id": "jL2ZME3Q", "type": "simple", + "id": "jL2ZME3Q", "question": "The movement of the aerodynamic centre of the wing when an aeroplane accelerates through the transonic range causes:", "options": [ { @@ -39460,12 +39460,12 @@ }, { "id": "Q95JQ9KNVY", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "97MYvHpb": { - "id": "97MYvHpb", "type": "simple", + "id": "97MYvHpb", "question": "When airflow over a wing becomes supersonic, the pressure pattern on the top surface will become?", "options": [ { @@ -39501,12 +39501,12 @@ }, { "id": "QA02G1JGTE", - "explanation": "", "learningObjectives": ["081.01.09.01.02"], + "explanation": "", "variants": { "a9LmSTHE": { - "id": "a9LmSTHE", "type": "simple", + "id": "a9LmSTHE", "question": "Compared to a wing with less camber, a more cambered wing will:", "options": [ { @@ -39542,12 +39542,12 @@ }, { "id": "QA7OCMVD67", - "explanation": "", "learningObjectives": ["081.01.01.04.04"], + "explanation": "", "variants": { "rRxOT81f": { - "id": "rRxOT81f", "type": "simple", + "id": "rRxOT81f", "question": "Maintaining thickness/chord ratio but changing to a\nsupercritical wing section will:", "options": [ { @@ -39583,12 +39583,12 @@ }, { "id": "QACJRZWTNF", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "kRVF0W4r": { - "id": "kRVF0W4r", "type": "simple", + "id": "kRVF0W4r", "question": "The critical Mach number of an aerofoil is the free stream Mach number at which:", "options": [ { @@ -39626,8 +39626,8 @@ "explanation": "" }, "eKkovAX5": { - "id": "eKkovAX5", "type": "simple", + "id": "eKkovAX5", "question": "The critical Mach number of an aerofoil is the free stream Mach number at which:", "options": [ { @@ -39660,8 +39660,8 @@ "explanation": "" }, "OabJxnui": { - "id": "OabJxnui", "type": "simple", + "id": "OabJxnui", "question": "The critical Mach number of an aerofoil is the free stream Mach number at which:", "options": [ { @@ -39697,12 +39697,12 @@ }, { "id": "QC6AFDJ374", - "explanation": "", "learningObjectives": ["081.01.02.03.01"], + "explanation": "", "variants": { "W7JJEaoG": { - "id": "W7JJEaoG", "type": "simple", + "id": "W7JJEaoG", "question": "The drag divergence Mach number of an aerofoil section is determined by:\n1) the angle of attack.\n2) the air pressure.\n3) the profile of the aerofoil.\n4) the air temperature.\nWhich answer combines all correct items?", "options": [ { @@ -39738,12 +39738,12 @@ }, { "id": "QDAYS1Z7CU", - "explanation": "", "learningObjectives": ["081.01.02.03.02"], + "explanation": "", "variants": { "rbFeZApt": { - "id": "rbFeZApt", "type": "simple", + "id": "rbFeZApt", "question": "Haemoglobin is", "options": [ { @@ -39779,12 +39779,12 @@ }, { "id": "QE2NP22PUY", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "c6rw2U7o": { - "id": "c6rw2U7o", "type": "simple", + "id": "c6rw2U7o", "question": "When an aerofoil section has accelerated from subsonic to supersonic speeds, its aerodynamic centre will have:", "options": [ { @@ -39820,12 +39820,12 @@ }, { "id": "QE68Q3VNKK", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "9rKf8CWM": { - "id": "9rKf8CWM", "type": "simple", + "id": "9rKf8CWM", "question": "If a symmetrical aerofoil is accelerated from subsonic to supersonic speed, the aerodynamic centre will move:", "options": [ { @@ -39861,12 +39861,12 @@ }, { "id": "QEH6B11G6L", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "iDRRPLC6": { - "id": "iDRRPLC6", "type": "simple", + "id": "iDRRPLC6", "question": "On a normally cambered airfoil which increases its speed through the transonic region, the lower shock wave...", "options": [ { @@ -39902,12 +39902,12 @@ }, { "id": "QGBRXJ89XH", - "explanation": "", "learningObjectives": ["081.01.10.01.02"], + "explanation": "", "variants": { "uBvTL4R2": { - "id": "uBvTL4R2", "type": "simple", + "id": "uBvTL4R2", "question": "When accelerating to the transonic range, C~LMAX~ will ___ and the 1g stalling speed will ___.", "options": [ { @@ -39943,12 +39943,12 @@ }, { "id": "QIUKW5SKCN", - "explanation": "", "learningObjectives": ["081.01.05.07.03"], + "explanation": "", "variants": { "ysBo6zZU": { - "id": "ysBo6zZU", "type": "simple", + "id": "ysBo6zZU", "question": "The speed range from approximately M = 1.3 to approximately M = 5 is called the:", "options": [ { @@ -39984,12 +39984,12 @@ }, { "id": "QK9WJGJDIB", - "explanation": "", "learningObjectives": ["081.01.09.03.01"], + "explanation": "", "variants": { "NPUWlFNx": { - "id": "NPUWlFNx", "type": "simple", + "id": "NPUWlFNx", "question": "Vortex generators on the upper side of the wing:", "options": [ { @@ -40025,12 +40025,12 @@ }, { "id": "QKZ6U54WK1", - "explanation": "", "learningObjectives": ["081.01.02.03.01"], + "explanation": "", "variants": { "29GnUoOa": { - "id": "29GnUoOa", "type": "simple", + "id": "29GnUoOa", "question": "The transonic region is where the local speeds on an aerofoil are:", "options": [ { @@ -40066,12 +40066,12 @@ }, { "id": "QL40NY3YIH", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "4EOpJI32": { - "id": "4EOpJI32", "type": "simple", + "id": "4EOpJI32", "question": "At a constant angle of attack, the coefficient of lift:", "options": [ { @@ -40107,12 +40107,12 @@ }, { "id": "QM7GAJTBLW", - "explanation": "", "learningObjectives": ["081.01.01.04.08"], + "explanation": "", "variants": { "3MhK8oJw": { - "id": "3MhK8oJw", "type": "simple", + "id": "3MhK8oJw", "question": "The marked nose down pitch occurs in the high transonic region when:", "options": [ { @@ -40148,12 +40148,12 @@ }, { "id": "QNFK5AK7Y4", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "5JFdSeTf": { - "id": "5JFdSeTf", "type": "simple", + "id": "5JFdSeTf", "question": "Which of the following I. aerofoils and II. angles of attack will produce the lowest Mcrit values?", "options": [ { @@ -40189,12 +40189,12 @@ }, { "id": "QNJ0SO4GHH", - "explanation": "", "learningObjectives": ["081.01.01.04.04"], + "explanation": "", "variants": { "eFsFN1R7": { - "id": "eFsFN1R7", "type": "simple", + "id": "eFsFN1R7", "question": "Reducing the thickness / chord ratio on a wing will:", "options": [ { @@ -40230,12 +40230,12 @@ }, { "id": "QNKMSKRSGL", - "explanation": "", "learningObjectives": ["081.01.04.02.03"], + "explanation": "", "variants": { "nRmhCLMw": { - "id": "nRmhCLMw", "type": "simple", + "id": "nRmhCLMw", "question": "Which of these statements about \"tuck under\" are correct or incorrect?\n1) A contributing factor to \"tuck under\" is a forward movement of the centre of pressure of the wing.\n2) A contributing factor to \"tuck under\" is an increase in the downwash angle at the location of the horizontal stabiliser.", "options": [ { @@ -40271,12 +40271,12 @@ }, { "id": "QO99SOPA34", - "explanation": "", "learningObjectives": ["081.01.03.03.02"], + "explanation": "", "variants": { "BHL0XiCH": { - "id": "BHL0XiCH", "type": "simple", + "id": "BHL0XiCH", "question": "How does the coefficient of drag change in the transonic region?", "options": [ { @@ -40312,12 +40312,12 @@ }, { "id": "QOBLCBGBIF", - "explanation": "", "learningObjectives": ["081.01.04.03.12"], + "explanation": "", "variants": { "73WDjYcj": { - "id": "73WDjYcj", "type": "simple", + "id": "73WDjYcj", "question": "A sharp increase in drag coefficient of a given wing or blade section at a constant angle of attack is determined by the:", "options": [ { @@ -40353,12 +40353,12 @@ }, { "id": "QP215M8VBN", - "explanation": "", "learningObjectives": ["081.01.12.02.01"], + "explanation": "", "variants": { "BjDP70sX": { - "id": "BjDP70sX", "type": "simple", + "id": "BjDP70sX", "question": "The application of the area rule on aeroplane design will decrease the", "options": [ { @@ -40394,12 +40394,12 @@ }, { "id": "QQ5Z5JAKYQ", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "6W0ClMeb": { - "id": "6W0ClMeb", "type": "simple", + "id": "6W0ClMeb", "question": "Which of the following wings will have the most effective high lift devices?", "options": [ { @@ -40435,12 +40435,12 @@ }, { "id": "QS59PM17DC", - "explanation": "", "learningObjectives": ["081.01.09.02.03"], + "explanation": "", "variants": { "HUT2BkVr": { - "id": "HUT2BkVr", "type": "simple", + "id": "HUT2BkVr", "question": "Compaired to a wing with less camber, a wing with greater camber will:", "options": [ { @@ -40473,8 +40473,8 @@ "explanation": "" }, "R6hdMF1a": { - "id": "R6hdMF1a", "type": "simple", + "id": "R6hdMF1a", "question": "Compaired to a wing with less camber, a wing with greater camber will:", "options": [ { @@ -40510,12 +40510,12 @@ }, { "id": "QSALCPHW9G", - "explanation": "", "learningObjectives": ["081.01.04.03.02"], + "explanation": "", "variants": { "ycKVDpNg": { - "id": "ycKVDpNg", "type": "simple", + "id": "ycKVDpNg", "question": "The drag coefficient at constant angle of attack:", "options": [ { @@ -40548,8 +40548,8 @@ "explanation": "" }, "N5Wxql8L": { - "id": "N5Wxql8L", "type": "simple", + "id": "N5Wxql8L", "question": "The drag coefficient at constant angle of attack:", "options": [ { @@ -40585,12 +40585,12 @@ }, { "id": "QSPM6ZSSCB", - "explanation": "", "learningObjectives": ["081.01.09.03.01"], + "explanation": "", "variants": { "QDsrRYoN": { - "id": "QDsrRYoN", "type": "simple", + "id": "QDsrRYoN", "question": "At speeds above the critical Mach number, vortex generators fitted to a wing's upper surface will...", "options": [ { @@ -40626,12 +40626,12 @@ }, { "id": "QTHPB5M1YM", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "8DYkp1Dm": { - "id": "8DYkp1Dm", "type": "simple", + "id": "8DYkp1Dm", "question": "A normal, cambered aerofoil accelerates to transonic speeds: the lower shockwave moves aft...", "options": [ { @@ -40667,12 +40667,12 @@ }, { "id": "QTKRNZ7AZP", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "XFyqBoRF": { - "id": "XFyqBoRF", "type": "simple", + "id": "XFyqBoRF", "question": "The wings which will have the most effective high lift devices are:", "options": [ { @@ -40708,12 +40708,12 @@ }, { "id": "QTY8HWMI45", - "explanation": "", "learningObjectives": ["081.01.04.03.04"], + "explanation": "", "variants": { "cEyvxXnz": { - "id": "cEyvxXnz", "type": "simple", + "id": "cEyvxXnz", "question": "What is the influence of decreasing aeroplane mass on Mcrit at constant IAS? (n=\n1)", "options": [ { @@ -40749,12 +40749,12 @@ }, { "id": "QV7XO5IVNI", - "explanation": "", "learningObjectives": ["081.01.04.03.02"], + "explanation": "", "variants": { "jMv4w3zU": { - "id": "jMv4w3zU", "type": "simple", + "id": "jMv4w3zU", "question": "If the angle of attack is constant, the drag coefficient:", "options": [ { @@ -40790,12 +40790,12 @@ }, { "id": "QVMCAEQVXB", - "explanation": "", "learningObjectives": ["081.01.04.03.04"], + "explanation": "", "variants": { "uvpDwNXG": { - "id": "uvpDwNXG", "type": "simple", + "id": "uvpDwNXG", "question": "What is the influence of decreasing aeroplane mass on M~CRIT~ at constant IAS? (n=1)", "options": [ { @@ -40831,12 +40831,12 @@ }, { "id": "QWVRUNW8UN", - "explanation": "", "learningObjectives": ["081.01.09.02.01"], + "explanation": "", "variants": { "0JSpUTJC": { - "id": "0JSpUTJC", "type": "simple", + "id": "0JSpUTJC", "question": "Compare the following wing designs and choose the one with the least effective high lift devices:\n(note: airspeed and all other factors remain unchanged)", "options": [ { @@ -40872,12 +40872,12 @@ }, { "id": "QZPDWFACXK", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "zJ9l9AlT": { - "id": "zJ9l9AlT", "type": "simple", + "id": "zJ9l9AlT", "question": "Which of the following (1) aerofoils and (2) angles of attack will produce the lowest MCRIT values?", "options": [ { @@ -40913,12 +40913,12 @@ }, { "id": "QYGDVMYNKB", - "explanation": "", "learningObjectives": ["081.01.01.02.01"], + "explanation": "", "variants": { "fGSJQEou": { - "id": "fGSJQEou", "type": "simple", + "id": "fGSJQEou", "question": "Airflow separation is characterised by:", "options": [ { @@ -40959,12 +40959,12 @@ }, { "id": "Q12CYPYQ9A", - "explanation": "", "learningObjectives": ["081.01.12.02.02"], + "explanation": "", "variants": { "oyaQwRvi": { - "id": "oyaQwRvi", "type": "simple", + "id": "oyaQwRvi", "question": "A boundary layer fence on a swept wing will improve the", "options": [ { @@ -41000,12 +41000,12 @@ }, { "id": "Q1F5XB1ELR", - "explanation": "", "learningObjectives": ["081.01.09.02.04"], + "explanation": "", "variants": { "5f6n8pCD": { - "id": "5f6n8pCD", "type": "simple", + "id": "5f6n8pCD", "question": "Which stall-detection device uses the movement of the leading-edge stagnation point to detect a stall?", "options": [ { @@ -41041,12 +41041,12 @@ }, { "id": "Q2UEE8LK4B", - "explanation": "", "learningObjectives": ["081.01.01.05.05"], + "explanation": "", "variants": { "dqTrNLUU": { - "id": "dqTrNLUU", "type": "simple", + "id": "dqTrNLUU", "question": "Which of the following statement correctly describes wing fences?", "options": [ { @@ -41082,12 +41082,12 @@ }, { "id": "Q4JVGGOJP1", - "explanation": "", "learningObjectives": ["081.01.12.01.03"], + "explanation": "", "variants": { "5rkFDeGE": { - "id": "5rkFDeGE", "type": "simple", + "id": "5rkFDeGE", "question": "An aircraft is de-iced on the ground in bad lighting conditions. After take-off, the crew is forced to apply higher than normal thrust to achieve the desired rate of climb. This is most likely due to...", "options": [ { @@ -41123,12 +41123,12 @@ }, { "id": "Q4ZVUIV8BG", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "5X209DI2": { - "id": "5X209DI2", "type": "simple", + "id": "5X209DI2", "question": "An aircraft is flying straight and level at 100 kts with a C~L~ of 0.35. Its C~Lmax~ is 1.22. Determine the maximum achievable load factor:", "options": [ { @@ -41164,12 +41164,12 @@ }, { "id": "Q6GJBBWJ4D", - "explanation": "", "learningObjectives": ["081.01.01.03.08"], + "explanation": "", "variants": { "kLsd9ZUB": { - "id": "kLsd9ZUB", "type": "simple", + "id": "kLsd9ZUB", "question": "When pulling out of a dive the angle of attack:", "options": [ { @@ -41205,12 +41205,12 @@ }, { "id": "Q916EU1SU4", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "E2Dyed5b": { - "id": "E2Dyed5b", "type": "simple", + "id": "E2Dyed5b", "question": "What is true regarding an aerofoil in a stalled condition?", "options": [ { @@ -41246,12 +41246,12 @@ }, { "id": "Q992YK9RXC", - "explanation": "", "learningObjectives": ["081.01.01.03.08"], + "explanation": "", "variants": { "7fppUShh": { - "id": "7fppUShh", "type": "simple", + "id": "7fppUShh", "question": "The critical angle of attack:", "options": [ { @@ -41293,12 +41293,12 @@ }, { "id": "QA0ND8QCUY", - "explanation": "", "learningObjectives": ["081.01.01.05.10"], + "explanation": "", "variants": { "UBq1CtXB": { - "id": "UBq1CtXB", "type": "simple", + "id": "UBq1CtXB", "question": "Which properties do swept wings have?", "options": [ { @@ -41334,12 +41334,12 @@ }, { "id": "QBKUBZELPD", - "explanation": "", "learningObjectives": ["081.01.09.01.09"], + "explanation": "", "variants": { "BqJ0duLQ": { - "id": "BqJ0duLQ", "type": "simple", + "id": "BqJ0duLQ", "question": "You are on an approach when extending flaps, due to a malfunction the right flap does not extend. What will happen to the aircraft?", "options": [ { @@ -41375,12 +41375,12 @@ }, { "id": "QBR9SQITU1", - "explanation": "", "learningObjectives": ["081.01.01.05.10"], + "explanation": "", "variants": { "x5GsjT6G": { - "id": "x5GsjT6G", "type": "simple", + "id": "x5GsjT6G", "question": "Wing sweep has", "options": [ { @@ -41416,12 +41416,12 @@ }, { "id": "QCLFLA34T6", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "9KfHUMoh": { - "id": "9KfHUMoh", "type": "simple", + "id": "9KfHUMoh", "question": "A multi engined commercial jet with underslung wing mounted engines is flying at the stall speed with idle power. If power is increased, C~LMAX~ will (1) _____ and the stall speed will (2) _____.", "options": [ { @@ -41457,12 +41457,12 @@ }, { "id": "QEGC6ZH9U8", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "2zeYSGic": { - "id": "2zeYSGic", "type": "simple", + "id": "2zeYSGic", "question": "When an aerofoil is stalled the lift/drag ratio is:", "options": [ { @@ -41498,12 +41498,12 @@ }, { "id": "QEMICSUVKX", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "sVN5rs5f": { - "id": "sVN5rs5f", "type": "simple", + "id": "sVN5rs5f", "question": "Which of the following statements about lift and drag at the stall is true?", "options": [ { @@ -41539,12 +41539,12 @@ }, { "id": "QF2QYS7M8F", - "explanation": "", "learningObjectives": ["081.01.09.01.02"], + "explanation": "", "variants": { "lrmaY5Ju": { - "id": "lrmaY5Ju", "type": "simple", + "id": "lrmaY5Ju", "question": "An increase in wing loading will:", "options": [ { @@ -41577,8 +41577,8 @@ "explanation": "" }, "mZ2khq4I": { - "id": "mZ2khq4I", "type": "simple", + "id": "mZ2khq4I", "question": "An increase in wing loading will:", "options": [ { @@ -41614,12 +41614,12 @@ }, { "id": "QFFKGYGDM0", - "explanation": "", "learningObjectives": ["081.01.12.01.03"], + "explanation": "", "variants": { "drJuDcyd": { - "id": "drJuDcyd", "type": "simple", + "id": "drJuDcyd", "question": "An aircraft is performing a take-off when it encounters windshear. What action should be taken?", "options": [ { @@ -41655,12 +41655,12 @@ }, { "id": "QG4TJVBCVP", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "4gILri4v": { - "id": "4gILri4v", "type": "simple", + "id": "4gILri4v", "question": "An aircraft has a mass of 304 tonnes including 75 tonnes of fuel at take-off. When it lands it has 8.5 tonnes of fuel remaining.\nIf its stalling speed was 100 kts on take-off, what will be its stalling speed on landing?", "options": [ { @@ -41696,12 +41696,12 @@ }, { "id": "QGITCOSXUS", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "NwD6Yxse": { - "id": "NwD6Yxse", "type": "simple", + "id": "NwD6Yxse", "question": "Just before the stalling angle of attack, what are the values of the lift coefficient and drag coefficient?", "options": [ { @@ -41737,12 +41737,12 @@ }, { "id": "QGSDNODVBK", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "KUFfZyPx": { - "id": "KUFfZyPx", "type": "simple", + "id": "KUFfZyPx", "question": "The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.4\n An increase in angle of attack of 1 degree will increase CL by 0.09\n A vertical up gust instantly changes the angle of attack by 5 degrees\n The load factor will be", "options": [ { @@ -41778,12 +41778,12 @@ }, { "id": "QHEP5KH26Z", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "yImtHRMK": { - "id": "yImtHRMK", "type": "simple", + "id": "yImtHRMK", "question": "The lift/drag ratio reaches its:", "options": [ { @@ -41816,8 +41816,8 @@ "explanation": "" }, "OchYLpeH": { - "id": "OchYLpeH", "type": "simple", + "id": "OchYLpeH", "question": "The lift/drag ratio reaches its:", "options": [ { @@ -41853,12 +41853,12 @@ }, { "id": "QICZX49PDS", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "FG0TurFg": { - "id": "FG0TurFg", "type": "simple", + "id": "FG0TurFg", "question": "The position of the transition point on an aerofoil is dependent on:", "options": [ { @@ -41894,12 +41894,12 @@ }, { "id": "QILPA3F54Z", - "explanation": "", "learningObjectives": ["081.01.09.03.01"], + "explanation": "", "variants": { "QFFAecGg": { - "id": "QFFAecGg", "type": "simple", + "id": "QFFAecGg", "question": "What are vortilons used for?", "options": [ { @@ -41935,12 +41935,12 @@ }, { "id": "QIWMP8JK1K", - "explanation": "", "learningObjectives": ["081.01.04.02.08"], + "explanation": "", "variants": { "yTmHoswG": { - "id": "yTmHoswG", "type": "simple", + "id": "yTmHoswG", "question": "Which of the following statements about wake turbulence are true?", "options": [ { @@ -41976,12 +41976,12 @@ }, { "id": "QJTUVMLY8B", - "explanation": "", "learningObjectives": ["081.01.04.02.03"], + "explanation": "", "variants": { "FjWQUWmL": { - "id": "FjWQUWmL", "type": "simple", + "id": "FjWQUWmL", "question": "Located on the underside of a wing’s leading edge, Vortilons produce a vortex on the wing’s...", "options": [ { @@ -42017,12 +42017,12 @@ }, { "id": "QL30PYIGIH", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "NbjVh4Am": { - "id": "NbjVh4Am", "type": "simple", + "id": "NbjVh4Am", "question": "An aircraft has a takeoff mass of 305 tonnes, and has burnt 63 tonnes of fuel when it starts its approach to land.\nIf Vs on take off was 140kts, what is its Vs at the start of the approach?", "options": [ { @@ -42058,12 +42058,12 @@ }, { "id": "QL62I4C08J", - "explanation": "", "learningObjectives": ["081.01.12.01.03"], + "explanation": "", "variants": { "NpH55ICb": { - "id": "NpH55ICb", "type": "simple", + "id": "NpH55ICb", "question": "When ice accretion builds up on the leading edge of the tailplane, the effect could be:", "options": [ { @@ -42099,12 +42099,12 @@ }, { "id": "QMVK367HG4", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "hztZI7wa": { - "id": "hztZI7wa", "type": "simple", + "id": "hztZI7wa", "question": "An aeroplane flying at a speed of 70 knots at Mean Sea Level produces a drag of 765 N. What will be this value at an altitude of 6000 ft, assuming that the speed and all the environmental factors remain constant ?", "options": [ { @@ -42140,12 +42140,12 @@ }, { "id": "QVT7XNTRNC", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "soY0R8hO": { - "id": "soY0R8hO", "type": "simple", + "id": "soY0R8hO", "question": "Compared with level flight prior to the stall, the lift (1) and drag (2) in the stall change as follows:", "options": [ { @@ -42181,12 +42181,12 @@ }, { "id": "QNWQ9F7Q4H", - "explanation": "", "learningObjectives": ["081.01.01.04.01"], + "explanation": "", "variants": { "4bPzo3Ud": { - "id": "4bPzo3Ud", "type": "simple", + "id": "4bPzo3Ud", "question": "That point where airflow leaves the surface of an aerofoil is known as:", "options": [ { @@ -42222,12 +42222,12 @@ }, { "id": "QPAQLAJOPE", - "explanation": "", "learningObjectives": ["081.01.01.05.10"], + "explanation": "", "variants": { "EqDbZD8R": { - "id": "EqDbZD8R", "type": "simple", + "id": "EqDbZD8R", "question": "The stalling angle of a wing:", "options": [ { @@ -42263,12 +42263,12 @@ }, { "id": "QPC0G9APOU", - "explanation": "", "learningObjectives": ["081.01.09.01.03"], + "explanation": "", "variants": { "Bh8EEsI2": { - "id": "Bh8EEsI2", "type": "simple", + "id": "Bh8EEsI2", "question": "When entering a stall, the Centre of Pressure (CP) will ___ on a straight wing and ___ on a strongly swept wing.", "options": [ { @@ -42304,12 +42304,12 @@ }, { "id": "QRIUI30WAF", - "explanation": "", "learningObjectives": ["081.01.01.05.10"], + "explanation": "", "variants": { "k6M8voFt": { - "id": "k6M8voFt", "type": "simple", + "id": "k6M8voFt", "question": "Which of these statements about the effect of wing sweep on centre of pressure location are correct or incorrect?\n1) The centre of pressure on a straight wing moves aft as the angle of attack approaches and exceeds the critical angle of attack.\n2) The centre of pressure on a strongly swept back wing moves forward as the angle of attack approaches and exceeds the critical angle of attack.", "options": [ { @@ -42350,12 +42350,12 @@ }, { "id": "QRTSWAR860", - "explanation": "", "learningObjectives": ["081.01.01.01.02"], + "explanation": "", "variants": { "4ogfx5O9": { - "id": "4ogfx5O9", "type": "simple", + "id": "4ogfx5O9", "question": " \n At a mass of 140 tons:", "options": [ { @@ -42388,8 +42388,8 @@ "explanation": "" }, "4kSobo0a": { - "id": "4kSobo0a", "type": "simple", + "id": "4kSobo0a", "question": " \n At a mass of 140 tons:", "options": [ { @@ -42422,8 +42422,8 @@ "explanation": "" }, "8O1jVkAY": { - "id": "8O1jVkAY", "type": "simple", + "id": "8O1jVkAY", "question": " \n At a mass of 140 tons:", "options": [ { @@ -42459,12 +42459,12 @@ }, { "id": "QV2T6U807Y", - "explanation": "", "learningObjectives": ["081.01.12.01.03"], + "explanation": "", "variants": { "rh60mx1P": { - "id": "rh60mx1P", "type": "simple", + "id": "rh60mx1P", "question": "Unless the Aircraft Manual permits otherwise, before take-off the regulations require:", "options": [ { @@ -42500,12 +42500,12 @@ }, { "id": "QXDFRS3WVE", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "HOmqjeTE": { - "id": "HOmqjeTE", "type": "simple", + "id": "HOmqjeTE", "question": "Where, on a convential low speed aerofoil, will flow separation normally start as angle of attack is increased?", "options": [ { @@ -42541,12 +42541,12 @@ }, { "id": "QXT6J70RR3", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "Kuit2C69": { - "id": "Kuit2C69", "type": "simple", + "id": "Kuit2C69", "question": "Compared with level flight prior to the stall, the lift ___ and drag ___ in the stall change.", "options": [ { @@ -42582,12 +42582,12 @@ }, { "id": "QY4SYHX28R", - "explanation": "", "learningObjectives": ["081.01.05.07.03"], + "explanation": "", "variants": { "UMYTTa4L": { - "id": "UMYTTa4L", "type": "simple", + "id": "UMYTTa4L", "question": "The speed range between high- and low speed buffet", "options": [ { @@ -42623,12 +42623,12 @@ }, { "id": "QYDDE5WG66", - "explanation": "", "learningObjectives": ["081.01.12.01.02"], + "explanation": "", "variants": { "PdGhS33I": { - "id": "PdGhS33I", "type": "simple", + "id": "PdGhS33I", "question": "What is the effect of icing or other airframe contaminants on the value of CLMAX, stall speed, and critical angle of attack? \n The CLMAX...", "options": [ { @@ -42664,12 +42664,12 @@ }, { "id": "QZ5A9WZ2RU", - "explanation": "", "learningObjectives": ["081.01.04.02.05"], + "explanation": "", "variants": { "Ywc208TM": { - "id": "Ywc208TM", "type": "simple", + "id": "Ywc208TM", "question": "The wing planform that gives the best progressive span wise stall development is the......wing:", "options": [ { @@ -42705,12 +42705,12 @@ }, { "id": "QZDPZP2JDF", - "explanation": "", "learningObjectives": ["081.01.03.02.01"], + "explanation": "", "variants": { "xpy8b7FX": { - "id": "xpy8b7FX", "type": "simple", + "id": "xpy8b7FX", "question": "A light airplane in clean configuration is making a turn in level flight. Given a load factor of 1.15 during the turn, calculate the change in the lift coefficient:", "options": [ { @@ -42746,12 +42746,12 @@ }, { "id": "Q0JEV8D2XQ", - "explanation": "", "learningObjectives": ["081.01.03.02.02"], + "explanation": "", "variants": { "K5sJGTul": { - "id": "K5sJGTul", "type": "simple", + "id": "K5sJGTul", "question": "How does positive camber of an aerofoil affect static longitudinal stability?", "options": [ { @@ -42787,12 +42787,12 @@ }, { "id": "Q0N3I6QHV9", - "explanation": "", "learningObjectives": ["081.01.01.05.09"], + "explanation": "", "variants": { "3CE1yf50": { - "id": "3CE1yf50", "type": "simple", + "id": "3CE1yf50", "question": "The \"dihedral\" construction feature of an aircraft wing provides an increase in:", "options": [ { @@ -42828,12 +42828,12 @@ }, { "id": "Q2KVYCHYBQ", - "explanation": "", "learningObjectives": ["081.01.01.03.01"], + "explanation": "", "variants": { "WIRtXmyX": { - "id": "WIRtXmyX", "type": "simple", + "id": "WIRtXmyX", "question": "The aft movement of the centre of pressure during the acceleration through the transonic flight regime will:", "options": [ { @@ -42869,12 +42869,12 @@ }, { "id": "QE8GSSTXP6", - "explanation": "", "learningObjectives": ["081.01.01.05.09"], + "explanation": "", "variants": { "q9PjpCGO": { - "id": "q9PjpCGO", "type": "simple", + "id": "q9PjpCGO", "question": "Wing dihedral:", "options": [ { @@ -42915,12 +42915,12 @@ }, { "id": "Q462IKGRS1", - "explanation": "", "learningObjectives": ["081.01.01.05.09"], + "explanation": "", "variants": { "ei5qB1hv": { - "id": "ei5qB1hv", "type": "simple", + "id": "ei5qB1hv", "question": "Geometric dihedral is the amount that the wings are actually “bent” up. In a sideslip to the right geometric dihedral will:\n ", "options": [ { @@ -42956,12 +42956,12 @@ }, { "id": "QHBLRLGNV0", - "explanation": "", "learningObjectives": ["081.01.01.05.09"], + "explanation": "", "variants": { "C62X56KF": { - "id": "C62X56KF", "type": "simple", + "id": "C62X56KF", "question": "The primary purpose of dihedral is to:", "options": [ { @@ -43002,12 +43002,12 @@ }, { "id": "QXNMMKMGD4", - "explanation": "", "learningObjectives": ["081.01.01.05.09"], + "explanation": "", "variants": { "WTXPwGVq": { - "id": "WTXPwGVq", "type": "simple", + "id": "WTXPwGVq", "question": "The effect of a high wing with zero dihedral is as follows:", "options": [ { @@ -43043,12 +43043,12 @@ }, { "id": "QM7BFIY960", - "explanation": "", "learningObjectives": ["081.01.12.02.01"], + "explanation": "", "variants": { "qJZOGPuR": { - "id": "qJZOGPuR", "type": "simple", + "id": "qJZOGPuR", "question": "After an aeroplane has been trimmed", "options": [ { @@ -43084,12 +43084,12 @@ }, { "id": "QNWJJ33TPZ", - "explanation": "", "learningObjectives": ["081.01.05.07.03"], + "explanation": "", "variants": { "dFrk2TFo": { - "id": "dFrk2TFo", "type": "simple", + "id": "dFrk2TFo", "question": "What is true of stability, with respect to velocity, in the transonic range?", "options": [ { @@ -43125,12 +43125,12 @@ }, { "id": "QO669WLUC7", - "explanation": "", "learningObjectives": ["081.01.12.02.01"], + "explanation": "", "variants": { "kO2bvYkr": { - "id": "kO2bvYkr", "type": "simple", + "id": "kO2bvYkr", "question": "Aeroplane manoeuvrability decreases for a given control surface deflection when", "options": [ { @@ -43169,8 +43169,8 @@ "explanation": "" }, "arKwgekU": { - "id": "arKwgekU", "type": "simple", + "id": "arKwgekU", "question": "Aeroplane manoeuvrability increases for a given control surface deflection when", "options": [ { @@ -43206,12 +43206,12 @@ }, { "id": "QOZ2PU081M", - "explanation": "", "learningObjectives": ["081.01.09.02.02"], + "explanation": "", "variants": { "eItCFQZa": { - "id": "eItCFQZa", "type": "simple", + "id": "eItCFQZa", "question": "The primary function of the fin is to give:", "options": [ { @@ -43247,12 +43247,12 @@ }, { "id": "QPK1KSZIJV", - "explanation": "", "learningObjectives": ["081.01.12.02.01"], + "explanation": "", "variants": { "bRCzwBBx": { - "id": "bRCzwBBx", "type": "simple", + "id": "bRCzwBBx", "question": "Which aeroplane behaviour will be corrected by a yaw damper?", "options": [ { @@ -43285,8 +43285,8 @@ "explanation": "" }, "mGJnT65S": { - "id": "mGJnT65S", "type": "simple", + "id": "mGJnT65S", "question": "Which aeroplane behaviour will be corrected by a yaw damper?", "options": [ { @@ -43322,12 +43322,12 @@ }, { "id": "QUD8ID1U16", - "explanation": "", "learningObjectives": ["081.01.01.03.04"], + "explanation": "", "variants": { "i0uzmNuj": { - "id": "i0uzmNuj", "type": "simple", + "id": "i0uzmNuj", "question": "If the sum of moments in flight is not zero, the aeroplane will rotate about the:", "options": [ { @@ -43368,12 +43368,12 @@ }, { "id": "QXT65DVJIC", - "explanation": "", "learningObjectives": ["081.01.01.05.09"], + "explanation": "", "variants": { "kZ2QBcuQ": { - "id": "kZ2QBcuQ", "type": "simple", + "id": "kZ2QBcuQ", "question": "Which of the following statements about dihedral is correct?", "options": [ { @@ -43409,12 +43409,12 @@ }, { "id": "Q3OZODQV5Y", - "explanation": "", "learningObjectives": ["081.01.09.01.07"], + "explanation": "", "variants": { "94KqYN8p": { - "id": "94KqYN8p", "type": "simple", + "id": "94KqYN8p", "question": "Trailing edge flap type flying controls work by altering:", "options": [ { @@ -43450,12 +43450,12 @@ }, { "id": "Q6EBP0CA4J", - "explanation": "", "learningObjectives": ["081.01.04.03.05"], + "explanation": "", "variants": { "9c5eRtKw": { - "id": "9c5eRtKw", "type": "simple", + "id": "9c5eRtKw", "question": "Which three aerodynamic means decrease manoeuvring stick forces?", "options": [ { @@ -43488,8 +43488,8 @@ "explanation": "" }, "UR3ImzzU": { - "id": "UR3ImzzU", "type": "simple", + "id": "UR3ImzzU", "question": "Which three aerodynamic means decrease manoeuvring stick forces?", "options": [ { @@ -43525,12 +43525,12 @@ }, { "id": "QOUOF0DALO", - "explanation": "", "learningObjectives": ["081.01.04.03.05"], + "explanation": "", "variants": { "8uVKxZvS": { - "id": "8uVKxZvS", "type": "simple", + "id": "8uVKxZvS", "question": "Which aerodynamic design features can be used to reduce control forces?", "options": [ { @@ -43571,12 +43571,12 @@ }, { "id": "QCBSZW495Z", - "explanation": "", "learningObjectives": ["081.01.12.02.01"], + "explanation": "", "variants": { "VNUaO0IG": { - "id": "VNUaO0IG", "type": "simple", + "id": "VNUaO0IG", "question": "How does the exterior view of an aeroplane change, when the trim is used during a speed decrease?", "options": [ { @@ -43612,12 +43612,12 @@ }, { "id": "QIUHL99KA3", - "explanation": "", "learningObjectives": ["081.01.12.02.01"], + "explanation": "", "variants": { "482v89Yu": { - "id": "482v89Yu", "type": "simple", + "id": "482v89Yu", "question": "How would the exterior appearance of an aeroplane change, when trimming for speed increase?", "options": [ { @@ -43653,12 +43653,12 @@ }, { "id": "QN2EJGDZS4", - "explanation": "", "learningObjectives": ["081.01.01.03.07"], + "explanation": "", "variants": { "cnGWFuJ2": { - "id": "cnGWFuJ2", "type": "simple", + "id": "cnGWFuJ2", "question": "Consider a symmetrical wing with a control surface in the trailing edge. When the control surface is deflected downwards, it (1) _____ the camber, producing a force in the (2) _____ direction of the deflection.", "options": [ { @@ -43694,12 +43694,12 @@ }, { "id": "QNY15HYWSF", - "explanation": "", "learningObjectives": ["081.01.10.01.01"], + "explanation": "", "variants": { "wDC79fcX": { - "id": "wDC79fcX", "type": "simple", + "id": "wDC79fcX", "question": "Spoilers installed on a typical large transport aeroplane are:", "options": [ { @@ -43735,12 +43735,12 @@ }, { "id": "Q18ZYNDOE5", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "u9QecIM8": { - "id": "u9QecIM8", "type": "simple", + "id": "u9QecIM8", "question": "If an aircraft is flying at 1.1 V~S~ with CL of 1.22 and the aircraft increases the speed to 1.8 V~S~, what is the new C~L~?", "options": [ { @@ -43776,12 +43776,12 @@ }, { "id": "QTMBSF0RR0", - "explanation": "", "learningObjectives": ["081.01.01.05.05"], + "explanation": "", "variants": { "6O4iVF90": { - "id": "6O4iVF90", "type": "simple", + "id": "6O4iVF90", "question": "What wing shape or wing characteristic is the least sensitive to turbulence?", "options": [ { @@ -43822,12 +43822,12 @@ }, { "id": "Q8C7MOIZGW", - "explanation": "", "learningObjectives": ["081.01.12.02.01"], + "explanation": "", "variants": { "UwduJRt2": { - "id": "UwduJRt2", "type": "simple", + "id": "UwduJRt2", "question": "This question does not apply to students of the new 2020 Syllabus\nFlutter sensitivity of an aeroplane wing is reduced by:", "options": [ { @@ -43863,12 +43863,12 @@ }, { "id": "Q91Q33LE4I", - "explanation": "", "learningObjectives": ["081.01.05.07.01"], + "explanation": "", "variants": { "PQ9dOhPK": { - "id": "PQ9dOhPK", "type": "simple", + "id": "PQ9dOhPK", "question": "How does the V~A~ change if the the aeroplane's mass decreases with 20%?", "options": [ { @@ -43904,12 +43904,12 @@ }, { "id": "QA6K8GH0V6", - "explanation": "", "learningObjectives": ["081.01.05.07.01"], + "explanation": "", "variants": { "CUfVnAhw": { - "id": "CUfVnAhw", "type": "simple", + "id": "CUfVnAhw", "question": "Your aircraft weight is reduced from 70 000 kg to 30 000 kg, how will this affect the gust load?", "options": [ { @@ -43945,12 +43945,12 @@ }, { "id": "QDHOTXLN21", - "explanation": "", "learningObjectives": ["081.01.01.05.04"], + "explanation": "", "variants": { "BkfOMuzO": { - "id": "BkfOMuzO", "type": "simple", + "id": "BkfOMuzO", "question": "Wing flutter may be caused by a:", "options": [ { @@ -43992,12 +43992,12 @@ }, { "id": "QD9045Y1XB", - "explanation": "", "learningObjectives": ["081.01.12.02.01"], + "explanation": "", "variants": { "75vM9BVY": { - "id": "75vM9BVY", "type": "simple", + "id": "75vM9BVY", "question": "What is the most important factor contributing to the drag increase that is observed with airframe ageing?", "options": [ { @@ -44033,12 +44033,12 @@ }, { "id": "QEPN1LP92P", - "explanation": "", "learningObjectives": ["081.01.05.07.01"], + "explanation": "", "variants": { "BTijq3qx": { - "id": "BTijq3qx", "type": "simple", + "id": "BTijq3qx", "question": "How does V~A~ (EAS) alter when the aeroplane’s mass decreases by 19%?", "options": [ { @@ -44074,12 +44074,12 @@ }, { "id": "QGFH5VXR33", - "explanation": "", "learningObjectives": ["081.01.05.07.03"], + "explanation": "", "variants": { "vvYxsPxJ": { - "id": "vvYxsPxJ", "type": "simple", + "id": "vvYxsPxJ", "question": "Which of the following statements about speeds is correct?", "options": [ { @@ -44115,12 +44115,12 @@ }, { "id": "QGV72704GJ", - "explanation": "", "learningObjectives": ["081.01.05.07.01"], + "explanation": "", "variants": { "AF7M1bcA": { - "id": "AF7M1bcA", "type": "simple", + "id": "AF7M1bcA", "question": "An aircraft is taking off, its V~A~ is 260 kt. If weight decreases by 20%, the new V~A~ will be...", "options": [ { @@ -44156,12 +44156,12 @@ }, { "id": "QI495M6DV8", - "explanation": "", "learningObjectives": ["081.01.04.03.05"], + "explanation": "", "variants": { "SX53tK7b": { - "id": "SX53tK7b", "type": "simple", + "id": "SX53tK7b", "question": "Flutter sensitivity of an aeroplane wing is reduced by:", "options": [ { @@ -44197,12 +44197,12 @@ }, { "id": "QIBXX0XFLG", - "explanation": "", "learningObjectives": ["081.01.05.07.03"], + "explanation": "", "variants": { "zyvCGMx7": { - "id": "zyvCGMx7", "type": "simple", + "id": "zyvCGMx7", "question": "The speed V~C ~ is:", "options": [ { @@ -44238,12 +44238,12 @@ }, { "id": "QVWMVPXA98", - "explanation": "", "learningObjectives": ["081.01.05.07.03"], + "explanation": "", "variants": { "HM90gZlE": { - "id": "HM90gZlE", "type": "simple", + "id": "HM90gZlE", "question": "The Never Exceed Speed (V~NE~) is set...", "options": [ { @@ -44279,12 +44279,12 @@ }, { "id": "QW6HK4681K", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "z7wbC9EX": { - "id": "z7wbC9EX", "type": "simple", + "id": "z7wbC9EX", "question": "An airplane is flying at 1.4 V~A~ and it decreases to 1.1 V~A~, by what percentage does the C~L~ increase?", "options": [ { @@ -44320,12 +44320,12 @@ }, { "id": "Q30W0JR1G6", - "explanation": "", "learningObjectives": ["081.01.01.05.09"], + "explanation": "", "variants": { "9BuIj3aN": { - "id": "9BuIj3aN", "type": "simple", + "id": "9BuIj3aN", "question": "Refer to figure 081-31.\nRefer to the attached figure. What angle is depicted by letter \"D\"?", "options": [ { @@ -44361,12 +44361,12 @@ }, { "id": "QMYMOGKQRZ", - "explanation": "", "learningObjectives": ["081.01.09.01.02"], + "explanation": "", "variants": { "x7HGIF91": { - "id": "x7HGIF91", "type": "simple", + "id": "x7HGIF91", "question": "Increasing the camber on propeller blades will, if all else is the same:", "options": [ { @@ -44399,8 +44399,8 @@ "explanation": "" }, "ZHkrCo5F": { - "id": "ZHkrCo5F", "type": "simple", + "id": "ZHkrCo5F", "question": "Increasing the camber on propeller blades will, if all\nelse is the same:", "options": [ { @@ -44436,12 +44436,12 @@ }, { "id": "QOY0PVI4CS", - "explanation": "", "learningObjectives": ["081.01.01.03.08"], + "explanation": "", "variants": { "RwOyVcIO": { - "id": "RwOyVcIO", "type": "simple", + "id": "RwOyVcIO", "question": "Refer to figure 081-31.\nIn the attached diagram, select the letter which correctly represents the Angle of Advance (Helix Angle):", "options": [ { @@ -44477,12 +44477,12 @@ }, { "id": "QRVHFHKMTQ", - "explanation": "", "learningObjectives": ["081.01.01.05.09"], + "explanation": "", "variants": { "f1z4Tono": { - "id": "f1z4Tono", "type": "simple", + "id": "f1z4Tono", "question": "Refer to the image. \nThe diagram the letter which correctly represents the Angle of Advance (Helix Angle) is:", "options": [ { @@ -44518,12 +44518,12 @@ }, { "id": "QXKGAVR1IY", - "explanation": "", "learningObjectives": ["081.01.01.03.08"], + "explanation": "", "variants": { "QPuFgmb8": { - "id": "QPuFgmb8", "type": "simple", + "id": "QPuFgmb8", "question": "Refer to figure 081-31.\nIn the attached diagram, select the letter which correctly represents the Angle of Attack:", "options": [ { @@ -44559,12 +44559,12 @@ }, { "id": "Q0YFZTTY5D", - "explanation": "", "learningObjectives": ["081.01.09.01.06"], + "explanation": "", "variants": { "Iod7Den4": { - "id": "Iod7Den4", "type": "simple", + "id": "Iod7Den4", "question": "The maximum glide range is achieved at _______ with an angle of attack of about 4°.", "options": [ { @@ -44600,12 +44600,12 @@ }, { "id": "Q1OQQUWCQC", - "explanation": "", "learningObjectives": ["081.01.01.01.09"], + "explanation": "", "variants": { "cOVUnyyU": { - "id": "cOVUnyyU", "type": "simple", + "id": "cOVUnyyU", "question": "What formula is used to measure work?", "options": [ { @@ -44641,12 +44641,12 @@ }, { "id": "Q1UOHR57DF", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "BfB2gRGP": { - "id": "BfB2gRGP", "type": "simple", + "id": "BfB2gRGP", "question": "If a pilot rolls to wings level from a level, co-ordinated turn and then maintains straight and level flight at the same altitude and does not change thrust, the speed will:", "options": [ { @@ -44682,12 +44682,12 @@ }, { "id": "Q3AGK6IN6R", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "UJyJy9U0": { - "id": "UJyJy9U0", "type": "simple", + "id": "UJyJy9U0", "question": "Refer to the Annex. \nWhich point in the diagram gives the lowest speed in horizontal flight?", "options": [ { @@ -44723,12 +44723,12 @@ }, { "id": "Q4PIMKHFT0", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "qn6AhBlQ": { - "id": "qn6AhBlQ", "type": "simple", + "id": "qn6AhBlQ", "question": "In a glide lift will be:", "options": [ { @@ -44764,12 +44764,12 @@ }, { "id": "Q57WTPDL0W", - "explanation": "", "learningObjectives": ["081.01.04.03.11"], + "explanation": "", "variants": { "QRlrQkkz": { - "id": "QRlrQkkz", "type": "simple", + "id": "QRlrQkkz", "question": "The lift to drag ratio determines the", "options": [ { @@ -44805,12 +44805,12 @@ }, { "id": "Q5CU29ULG9", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "prBT7I7v": { - "id": "prBT7I7v", "type": "simple", + "id": "prBT7I7v", "question": "An aircraft is climbing at an angle of 9 degrees with a weight of 1 250 000 N, drag of 300 000 N and a thrust of 600 000 N.\n \nThe lift is roughly:", "options": [ { @@ -44846,12 +44846,12 @@ }, { "id": "Q5JGQVJU83", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "k796T8ML": { - "id": "k796T8ML", "type": "simple", + "id": "k796T8ML", "question": "The lift to drag ratio is highest when the flight speed is", "options": [ { @@ -44887,12 +44887,12 @@ }, { "id": "QL57UQA78S", - "explanation": "", "learningObjectives": ["081.01.01.04.06"], + "explanation": "", "variants": { "sZZ6CVmK": { - "id": "sZZ6CVmK", "type": "simple", + "id": "sZZ6CVmK", "question": "The parameters that can be read from the aeroplane parabolic polar curve are the:", "options": [ { @@ -44933,12 +44933,12 @@ }, { "id": "Q6Y98QJ0ZZ", - "explanation": "", "learningObjectives": ["081.01.01.04.03"], + "explanation": "", "variants": { "6ef83iCT": { - "id": "6ef83iCT", "type": "simple", + "id": "6ef83iCT", "question": "Which of the following parameters can be read from the parabolic Polar diagram of an aeroplane?", "options": [ { @@ -44974,12 +44974,12 @@ }, { "id": "Q84GSWTBI0", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "OnzUAMti": { - "id": "OnzUAMti", "type": "simple", + "id": "OnzUAMti", "question": "The four forces of lift, weight, thrust and drag in level flight act through:", "options": [ { @@ -45015,12 +45015,12 @@ }, { "id": "Q84JF5RJ43", - "explanation": "", "learningObjectives": ["081.01.12.01.02"], + "explanation": "", "variants": { "lAwstJoI": { - "id": "lAwstJoI", "type": "simple", + "id": "lAwstJoI", "question": "What words must be used to complete the statement below? \nA wing, contaminated with ice, will typically stall at __\n1) Angle Of Attack (AOA) and at __\n2) airspeed, with small amounts of ice having already an effect, whereby the effect __\n3) if the ice is rough.", "options": [ { @@ -45056,12 +45056,12 @@ }, { "id": "Q8707YE25D", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "8hfw51WX": { - "id": "8hfw51WX", "type": "simple", + "id": "8hfw51WX", "question": "Refer to figure 081-03.\nAssuming zero thrust, the point on the diagram corresponding to the value for minimum sink rate is:", "options": [ { @@ -45097,12 +45097,12 @@ }, { "id": "Q91X1AZH4R", - "explanation": "", "learningObjectives": ["081.01.03.02.05"], + "explanation": "", "variants": { "pmLjspG3": { - "id": "pmLjspG3", "type": "simple", + "id": "pmLjspG3", "question": "The point in the annex corresponding to CL for minimum horizontal flight speed is", "options": [ { @@ -45138,12 +45138,12 @@ }, { "id": "Q9626KN6KI", - "explanation": "", "learningObjectives": ["081.01.02.09.02"], + "explanation": "", "variants": { "1LdFLswK": { - "id": "1LdFLswK", "type": "simple", + "id": "1LdFLswK", "question": "Refer to figure 081-03.\nThe point in the figure corresponding to C~L~ for minimum horizontal flight speed is:", "options": [ { @@ -45179,12 +45179,12 @@ }, { "id": "QA40MNIZNQ", - "explanation": "", "learningObjectives": ["081.01.10.02.05"], + "explanation": "", "variants": { "sqhSMctT": { - "id": "sqhSMctT", "type": "simple", + "id": "sqhSMctT", "question": "During a steady glide, increasing descent angle will...", "options": [ { @@ -45220,12 +45220,12 @@ }, { "id": "QADCCBVHT3", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "5g8xho5J": { - "id": "5g8xho5J", "type": "simple", + "id": "5g8xho5J", "question": "Refer to figure 081-03.\nThe point on the diagram corresponding to the minimum value of the drag coefficient is:", "options": [ { @@ -45258,8 +45258,8 @@ "explanation": "" }, "3S1FOYCS": { - "id": "3S1FOYCS", "type": "simple", + "id": "3S1FOYCS", "question": "Refer to figure 081-03.\nThe point on the diagram corresponding to the minimum value of drag is:", "options": [ { @@ -45295,12 +45295,12 @@ }, { "id": "QAJ3LXRG71", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "zxDMP0Cq": { - "id": "zxDMP0Cq", "type": "simple", + "id": "zxDMP0Cq", "question": "Given:\nDrag: 103 500 N\nMass: 12 500 kg\nWhat is the lift in N if you are in a 30° degree gliding descent?", "options": [ { @@ -45336,12 +45336,12 @@ }, { "id": "QBV8JDU3WY", - "explanation": "", "learningObjectives": ["081.01.09.01.06"], + "explanation": "", "variants": { "Kz6SHkgY": { - "id": "Kz6SHkgY", "type": "simple", + "id": "Kz6SHkgY", "question": "Refer to figure. \n Assuming zero thrust, the point on the diagram corresponding to the minimum glide angle is:", "options": [ { @@ -45377,12 +45377,12 @@ }, { "id": "QDLPJ3T6G6", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "QUdU44aH": { - "id": "QUdU44aH", "type": "simple", + "id": "QUdU44aH", "question": "What factors determine the distance travelled over ground of an aeroplane in a glide from a given altitude?", "options": [ { @@ -45420,8 +45420,8 @@ "explanation": "" }, "v1Xop9aD": { - "id": "v1Xop9aD", "type": "simple", + "id": "v1Xop9aD", "question": "What factors determine the distance travelled over ground of an aeroplane in a glide from a given altitude?", "options": [ { @@ -45457,12 +45457,12 @@ }, { "id": "QDWIVR2GFZ", - "explanation": "", "learningObjectives": ["081.01.04.03.14"], + "explanation": "", "variants": { "rIVwdI1b": { - "id": "rIVwdI1b", "type": "simple", + "id": "rIVwdI1b", "question": "The point on the image corresponding to the minimum value of the drag coefficient is", "options": [ { @@ -45495,8 +45495,8 @@ "explanation": "" }, "gZe04f6R": { - "id": "gZe04f6R", "type": "simple", + "id": "gZe04f6R", "question": "The point on the image corresponding to the minimum value of drag is", "options": [ { @@ -45532,12 +45532,12 @@ }, { "id": "QDYNG34CQS", - "explanation": "", "learningObjectives": ["081.01.04.03.12"], + "explanation": "", "variants": { "61PbZ4GU": { - "id": "61PbZ4GU", "type": "simple", + "id": "61PbZ4GU", "question": "Given the following characteristic points on a jet engine aeroplane’s polar curve:\n1 - CL~MAX~.2 - long range cruise (zero wind).3 - maximum lift to drag ratio.4 - minimum rate of descent (assume zero thrust).5 - maximum range cruise (zero wind).\nArrange these points in order of increasing angle of attack:", "options": [ { @@ -45573,12 +45573,12 @@ }, { "id": "QFF39CJDUH", - "explanation": "", "learningObjectives": ["081.01.09.01.06"], + "explanation": "", "variants": { "KVivni6d": { - "id": "KVivni6d", "type": "simple", + "id": "KVivni6d", "question": "Refer to figure 081-49.\nAn aircraft in glide starts at line 2 position, if the pilot extend the flaps, what will be the path line that the aircraft will follow?", "options": [ { @@ -45614,12 +45614,12 @@ }, { "id": "QFW5W0C93C", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "Ujd9jArG": { - "id": "Ujd9jArG", "type": "simple", + "id": "Ujd9jArG", "question": "(For this question use the image in the annex). The point in the diagram giving the lowest speed in unaccelerated flight is:", "options": [ { @@ -45655,12 +45655,12 @@ }, { "id": "QGIR8K32RZ", - "explanation": "", "learningObjectives": ["081.01.05.07.01"], + "explanation": "", "variants": { "MxbQslco": { - "id": "MxbQslco", "type": "simple", + "id": "MxbQslco", "question": "Example question. An aircraft’s departure is delayed several hours due to technical problems. The OAT has increased significantly by the time it is ready for take-off. What is the effect on V~MCG ~ ?\r ", "options": [ { @@ -45696,12 +45696,12 @@ }, { "id": "QGO9WBY9MH", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "sgjLYOct": { - "id": "sgjLYOct", "type": "simple", + "id": "sgjLYOct", "question": "(For this question use the image in the annex). Assuming zero thrust, the point on the diagram corresponding to the value for minimum sink rate is:", "options": [ { @@ -45737,12 +45737,12 @@ }, { "id": "QHSG2WKNL2", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "xxO3WDOF": { - "id": "xxO3WDOF", "type": "simple", + "id": "xxO3WDOF", "question": "Which statement about minimum control speed is correct?", "options": [ { @@ -45775,8 +45775,8 @@ "explanation": "" }, "O74fSTIw": { - "id": "O74fSTIw", "type": "simple", + "id": "O74fSTIw", "question": "Which statement about minimum control speed is correct?", "options": [ { @@ -45809,8 +45809,8 @@ "explanation": "" }, "e2lOj4Kh": { - "id": "e2lOj4Kh", "type": "simple", + "id": "e2lOj4Kh", "question": "Which statement about minimum control speed is correct?", "options": [ { @@ -45846,12 +45846,12 @@ }, { "id": "QJ60RYTJOQ", - "explanation": "", "learningObjectives": ["081.01.10.02.05"], + "explanation": "", "variants": { "X0gcDPTD": { - "id": "X0gcDPTD", "type": "simple", + "id": "X0gcDPTD", "question": "During a steady glide, increasing descent angle will:", "options": [ { @@ -45887,12 +45887,12 @@ }, { "id": "QJAVJD9NUY", - "explanation": "", "learningObjectives": ["081.01.04.03.14"], + "explanation": "", "variants": { "RBXBDcPV": { - "id": "RBXBDcPV", "type": "simple", + "id": "RBXBDcPV", "question": " \n The point on the polar curve corresponding to flight with minimum drag is:", "options": [ { @@ -45928,12 +45928,12 @@ }, { "id": "QNT39T5V4L", - "explanation": "", "learningObjectives": ["081.01.05.07.01"], + "explanation": "", "variants": { "so0IVIVl": { - "id": "so0IVIVl", "type": "simple", + "id": "so0IVIVl", "question": "From a Polar diagram of the entire aeroplane in the clean configuration one can read:", "options": [ { @@ -45969,12 +45969,12 @@ }, { "id": "QTNRTTQJBB", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "in3vgw6a": { - "id": "in3vgw6a", "type": "simple", + "id": "in3vgw6a", "question": "Which statement is correct at the speed for minimum drag (subsonic)?", "options": [ { @@ -46007,8 +46007,8 @@ "explanation": "" }, "Tbjfy2ty": { - "id": "Tbjfy2ty", "type": "simple", + "id": "Tbjfy2ty", "question": "Which statement is correct at the speed for minimum drag (subsonic)?", "options": [ { @@ -46044,12 +46044,12 @@ }, { "id": "QPMGM9ZX5G", - "explanation": "", "learningObjectives": ["081.01.04.03.14"], + "explanation": "", "variants": { "MEfiRZlM": { - "id": "MEfiRZlM", "type": "simple", + "id": "MEfiRZlM", "question": "(For this question use the image in the annex). The point on the diagram corresponding to the minimum value of drag is:", "options": [ { @@ -46082,8 +46082,8 @@ "explanation": "" }, "0MS4O8fg": { - "id": "0MS4O8fg", "type": "simple", + "id": "0MS4O8fg", "question": "(For this question use the image in the annex). The point on the diagram corresponding to the minimum value of the drag coefficient is:", "options": [ { @@ -46119,12 +46119,12 @@ }, { "id": "QQH57JWJW3", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "7uku7sqP": { - "id": "7uku7sqP", "type": "simple", + "id": "7uku7sqP", "question": "Refer to figure 081-03.\nThe point in the diagram giving the lowest speed in unaccelerated horizontal flight is:", "options": [ { @@ -46160,12 +46160,12 @@ }, { "id": "QQMEFJ0184", - "explanation": "", "learningObjectives": ["081.01.03.02.01"], + "explanation": "", "variants": { "GX7QKHOl": { - "id": "GX7QKHOl", "type": "simple", + "id": "GX7QKHOl", "question": "How can you calculate the lift in a steady climb, if we disregard thrust?", "options": [ { @@ -46201,12 +46201,12 @@ }, { "id": "QR97W0X3VD", - "explanation": "", "learningObjectives": ["081.01.01.05.10"], + "explanation": "", "variants": { "THGt1vO2": { - "id": "THGt1vO2", "type": "simple", + "id": "THGt1vO2", "question": "Swept wings have the following properties:", "options": [ { @@ -46242,12 +46242,12 @@ }, { "id": "QS5PGVG3BH", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "hRfCQ24a": { - "id": "hRfCQ24a", "type": "simple", + "id": "hRfCQ24a", "question": "If a pilot initiates a level, co-ordinated turn from straight and level flight at the same altitude and does not change thrust, the speed will", "options": [ { @@ -46283,12 +46283,12 @@ }, { "id": "QS9BTV1RHB", - "explanation": "", "learningObjectives": ["081.01.06.04.01"], + "explanation": "", "variants": { "QeXq8WYJ": { - "id": "QeXq8WYJ", "type": "simple", + "id": "QeXq8WYJ", "question": "What decreases the maximum ground distance during a glide with zero thrust?", "options": [ { @@ -46321,8 +46321,8 @@ "explanation": "" }, "uuistak0": { - "id": "uuistak0", "type": "simple", + "id": "uuistak0", "question": "What decreases the maximum ground distance during a glide with zero thrust?", "options": [ { @@ -46355,8 +46355,8 @@ "explanation": "" }, "vxlHfcTP": { - "id": "vxlHfcTP", "type": "simple", + "id": "vxlHfcTP", "question": "What increases the maximum ground distance during a glide with zero thrust?", "options": [ { @@ -46392,12 +46392,12 @@ }, { "id": "QVDNEGFBUR", - "explanation": "", "learningObjectives": ["081.01.01.03.06"], + "explanation": "", "variants": { "DX2exZFb": { - "id": "DX2exZFb", "type": "simple", + "id": "DX2exZFb", "question": "When an aircraft with a typical aerofoil is in level flight at low speed and high angle of attack, the normal axis is:", "options": [ { @@ -46433,12 +46433,12 @@ }, { "id": "QVM15ET4J7", - "explanation": "", "learningObjectives": ["081.01.05.05.02"], + "explanation": "", "variants": { "3lgB7vfJ": { - "id": "3lgB7vfJ", "type": "simple", + "id": "3lgB7vfJ", "question": "Refer to figure 081-28.\nThe point in the annex corresponding to C~L~ for minimum horizontal flight speed is:", "options": [ { @@ -46477,12 +46477,12 @@ }, { "id": "QVM8081N9T", - "explanation": "", "learningObjectives": ["081.01.01.03.03"], + "explanation": "", "variants": { "zoG6jTFQ": { - "id": "zoG6jTFQ", "type": "simple", + "id": "zoG6jTFQ", "question": "Given:\nWeight: 100 500 N\nLift: 94 439 N\nThrust: 32 000 N\n \nWhat is the drag for an aircraft that is on a 20° descent?", "options": [ { @@ -46518,12 +46518,12 @@ }, { "id": "QX1TT5UFQB", - "explanation": "", "learningObjectives": ["081.01.02.06.02"], + "explanation": "", "variants": { "cgEQqiIa": { - "id": "cgEQqiIa", "type": "simple", + "id": "cgEQqiIa", "question": "What causes friction drag?", "options": [ { @@ -46559,12 +46559,12 @@ }, { "id": "QX6JUA4CUQ", - "explanation": "", "learningObjectives": ["081.01.07.01.01"], + "explanation": "", "variants": { "5pICPyty": { - "id": "5pICPyty", "type": "simple", + "id": "5pICPyty", "question": "An aircraft in straight and level flight enters a 30 degree turn with no change in airspeed. As a result, the load factor increases to 1.15. What is the value of the coefficient of lift, compared to straight and level flight?", "options": [ { @@ -46600,12 +46600,12 @@ }, { "id": "QYRT9AR8TS", - "explanation": "", "learningObjectives": ["081.01.05.07.03"], + "explanation": "", "variants": { "WRtMSY1r": { - "id": "WRtMSY1r", "type": "simple", + "id": "WRtMSY1r", "question": " \n The point in the diagram giving the lowest speed in unaccelerated flight is:", "options": [ { @@ -46641,12 +46641,12 @@ }, { "id": "QZDC2ALA9F", - "explanation": "", "learningObjectives": ["081.01.10.02.05"], + "explanation": "", "variants": { "fS5rYpL7": { - "id": "fS5rYpL7", "type": "simple", + "id": "fS5rYpL7", "question": "What would happen to an aircraft's rate of descent and the angle of descent when deploying the speed brakes in flight?", "options": [ {