Applies automatic ruff fixes.

aerosandbox/__init__.py

@@ -14,7 +14,7 @@
 from aerosandbox.propulsion import *
 from aerosandbox.structures import *
 
-__version__ = "4.2.5"
+__version__ = "4.2.6"
 
 
 def docs():

aerosandbox/aerodynamics/aero_2D/airfoil_inviscid.py

@@ -5,7 +5,7 @@
     calculate_induced_velocity_line_singularities,
 )
 import aerosandbox.numpy as np
-from typing import Union, List, Optional
+from typing import Union, List
 
 
 class AirfoilInviscid(ImplicitAnalysis):
@@ -246,7 +246,7 @@ def draw_streamlines(self, res=200, show=True):
         plt.gca().set_aspect("equal", adjustable="box")
         plt.xlabel(r"$x/c$")
         plt.ylabel(r"$y/c$")
-        plt.title(rf"Inviscid Airfoil: Flow Field")
+        plt.title(r"Inviscid Airfoil: Flow Field")
         plt.tight_layout()
         if show:
             plt.show()

aerosandbox/aerodynamics/aero_2D/airfoil_optimizer/airfoil_optimizer.py

@@ -3,7 +3,6 @@
 from aerosandbox.geometry.airfoil.airfoil_families import get_kulfan_coordinates
 from scipy import optimize
 import matplotlib.pyplot as plt
-import aerosandbox.tools.pretty_plots as p
 
 if __name__ == "__main__":
 

aerosandbox/aerodynamics/aero_2D/airfoil_polar_functions.py

@@ -1,7 +1,5 @@
 from aerosandbox.geometry import Airfoil
-from aerosandbox.performance import OperatingPoint
 import aerosandbox.numpy as np
-import aerosandbox.library.aerodynamics as aerolib
 
 
 def airfoil_coefficients_post_stall(

aerosandbox/aerodynamics/aero_2D/mses.py

@@ -4,12 +4,9 @@
 from pathlib import Path
 from aerosandbox.geometry import Airfoil
 from aerosandbox.aerodynamics.aero_3D.avl import AVL
-from typing import Union, List, Dict
+from typing import Union, List
 import tempfile
-import warnings
-import os
 from textwrap import dedent
-import shutil
 
 
 class MSES(ExplicitAnalysis):
@@ -329,7 +326,7 @@ def mset(mset_alpha):
                     continue
 
                 mplot_keystrokes = dedent(
-                    f"""\
+                    """\
                         1
                         12
                         0

aerosandbox/aerodynamics/aero_2D/test_aero_2D/test_neuralfoil_optimization.py

@@ -1,5 +1,4 @@
 import aerosandbox as asb
-import aerosandbox.numpy as np
 import pytest
 
 

aerosandbox/aerodynamics/aero_2D/xfoil.py

@@ -576,7 +576,7 @@ def open_interactive(self) -> None:
             self.airfoil.write_dat(directory / airfoil_file)
 
             ### Open up AVL
-            import sys, os
+            import sys
 
             if sys.platform == "win32":
                 # Run XFoil

aerosandbox/aerodynamics/aero_3D/aero_buildup.py

@@ -6,13 +6,11 @@
 from aerosandbox.aerodynamics.aero_3D.aero_buildup_submodels.fuselage_aerodynamics_utilities import *
 from aerosandbox.library.aerodynamics import transonic
 import aerosandbox.library.aerodynamics as aerolib
-import copy
-from typing import Union, List, Dict, Any
+from typing import Union, List, Dict
 from aerosandbox.aerodynamics.aero_3D.aero_buildup_submodels.softmax_scalefree import (
     softmax_scalefree,
 )
 from dataclasses import dataclass
-from functools import cached_property
 
 
 class AeroBuildup(ExplicitAnalysis):

aerosandbox/aerodynamics/aero_3D/avl.py

@@ -4,8 +4,7 @@
 from pathlib import Path
 from aerosandbox.geometry import Airplane, Wing, WingXSec, Fuselage, ControlSurface
 from aerosandbox.performance import OperatingPoint
-from typing import Union, List, Dict, Any
-import copy
+from typing import Union, List, Dict
 import tempfile
 import warnings
 
@@ -179,7 +178,7 @@ def open_interactive(self) -> None:
             self.write_avl(directory / airplane_file)
 
             ### Open up AVL
-            import sys, os
+            import sys
 
             if sys.platform == "win32":
                 # Run AVL
@@ -388,7 +387,7 @@ def _default_keystroke_file_contents(self) -> List[str]:
         ]
 
         # Set control surface deflections
-        run_file_contents += [f"d1 d1 1"]
+        run_file_contents += ["d1 d1 1"]
 
         return run_file_contents
 
@@ -471,7 +470,7 @@ def clean(s):
 
             if wing.symmetric:
                 avl_file += clean(
-                    f"""\
+                    """\
                 YDUPLICATE
                 0
                     
@@ -480,23 +479,23 @@ def clean(s):
 
             if wing_options["no_wake"]:
                 avl_file += clean(
-                    f"""\
+                    """\
                 NOWAKE
                 
                 """
                 )
 
             if wing_options["no_alpha_beta"]:
                 avl_file += clean(
-                    f"""\
+                    """\
                 NOALBE
                 
                 """
                 )
 
             if wing_options["no_load"]:
                 avl_file += clean(
-                    f"""\
+                    """\
                 NOLOAD
                 
                 """

aerosandbox/aerodynamics/aero_3D/lifting_line.py

@@ -7,7 +7,7 @@
 from aerosandbox.aerodynamics.aero_3D.singularities.point_source import (
     calculate_induced_velocity_point_source,
 )
-from typing import Dict, Any, List, Callable, Union
+from typing import Dict, List, Callable, Union
 from aerosandbox.aerodynamics.aero_3D.aero_buildup import AeroBuildup
 from dataclasses import dataclass
 
@@ -1323,8 +1323,6 @@ def get_aero(resolution):
     resolutions = 1 + np.arange(20)
     aeros = get_aero(resolutions)
 
-    import matplotlib.pyplot as plt
-    import aerosandbox.tools.pretty_plots as p
 
     fig, ax = plt.subplots(3, 1)
     ax[0].semilogx(resolutions, [aero["CL"] for aero in aeros])

aerosandbox/aerodynamics/aero_3D/linear_potential_flow.py

@@ -5,10 +5,8 @@
 from aerosandbox.aerodynamics.aero_3D.singularities.uniform_strength_horseshoe_singularities import (
     calculate_induced_velocity_horseshoe,
 )
-from typing import Dict, Any, List, Callable, Optional, Union, Tuple
-import copy
-from functools import cached_property, lru_cache, partial
-from collections import namedtuple
+from typing import Dict, Any, List, Union, Tuple
+from functools import cached_property, partial
 from dataclasses import dataclass
 from abc import abstractmethod, ABC
 

aerosandbox/aerodynamics/aero_3D/nonlinear_lifting_line.py

@@ -9,7 +9,6 @@
 )
 import aerosandbox.numpy as np
 from typing import Dict, Any, Callable, List
-import copy
 
 
 ### Define some helper functions that take a vector and make it a Nx1 or 1xN, respectively.

aerosandbox/aerodynamics/aero_3D/test_aero_3D/geometries/flat_plate.py

@@ -1,5 +1,4 @@
 import aerosandbox as asb
-import aerosandbox.numpy as np
 
 airfoil = asb.Airfoil("naca0008")
 

aerosandbox/aerodynamics/aero_3D/test_aero_3D/geometries/flat_plate_mirrored.py

@@ -1,5 +1,4 @@
 import aerosandbox as asb
-import aerosandbox.numpy as np
 
 airfoil = asb.Airfoil("naca0008")
 

aerosandbox/aerodynamics/aero_3D/test_aero_3D/test_aero_buildup/avl_validation.py

@@ -1,5 +1,4 @@
 import aerosandbox as asb
-import aerosandbox.numpy as np
 import pytest
 
 wing_airfoil = asb.Airfoil("naca0010")  # asb.Airfoil("sd7037")

aerosandbox/aerodynamics/aero_3D/test_aero_3D/test_aero_buildup/draw_fuselage_aero.py

@@ -24,7 +24,6 @@
     ),
 ).run()
 
-from aerosandbox.tools.string_formatting import eng_string
 
 p.contour(
     Beta,

aerosandbox/aerodynamics/aero_3D/test_aero_3D/test_aero_buildup/fuselage_moment_calculation.py

@@ -27,8 +27,6 @@ def get_aero(xyz_ref):
 x_cgs = np.linspace(0, 1, 11)
 aeros = np.array([get_aero(xyz_ref=[x, 0, 0]) for x in x_cgs], dtype="O")
 
-import matplotlib.pyplot as plt
-import aerosandbox.tools.pretty_plots as p
 
 fig, ax = plt.subplots(figsize=(4, 4))
 

aerosandbox/aerodynamics/aero_3D/test_aero_3D/test_aero_buildup/test_basic.py

@@ -1,5 +1,4 @@
 import aerosandbox as asb
-import pytest
 from aerosandbox.aerodynamics.aero_3D.test_aero_3D.geometries.conventional import (
     airplane,
 )

aerosandbox/aerodynamics/aero_3D/test_aero_3D/test_avl.py

@@ -1,5 +1,4 @@
 import aerosandbox as asb
-import pytest
 
 
 def is_tool(name):

aerosandbox/aerodynamics/aero_3D/test_aero_3D/test_lifting_line.py

@@ -1,8 +1,3 @@
-import aerosandbox as asb
-import pytest
-from aerosandbox.aerodynamics.aero_3D.test_aero_3D.geometries.conventional import (
-    airplane,
-)
 
 # def test_lifting_line():
 #     analysis = asb.LiftingLine(

aerosandbox/aerodynamics/aero_3D/test_aero_3D/test_vlm/avl_validation.py

@@ -2,7 +2,6 @@
     airplane,
 )
 import aerosandbox as asb
-import aerosandbox.numpy as np
 
 
 op_point = asb.OperatingPoint(velocity=25, alpha=3)

aerosandbox/aerodynamics/aero_3D/test_aero_3D/test_vlm/test_airplane_optimization.py

@@ -1,5 +1,4 @@
 import aerosandbox as asb
-import aerosandbox.numpy as np
 import pytest
 
 

aerosandbox/aerodynamics/aero_3D/test_aero_3D/test_vlm/test_operating_point_optimization.py

@@ -1,5 +1,4 @@
 import aerosandbox as asb
-import aerosandbox.numpy as np
 import pytest
 
 airplane = asb.Airplane(

aerosandbox/aerodynamics/aero_3D/test_aero_3D/test_vortex_lattice_method.py

@@ -1,5 +1,4 @@
 import aerosandbox as asb
-import pytest
 
 
 def test_conventional():

aerosandbox/atmosphere/_diff_atmo_functions.py

@@ -1,10 +1,8 @@
 import aerosandbox.numpy as np
-from pathlib import Path
 from aerosandbox.modeling.interpolation import InterpolatedModel
 from aerosandbox.atmosphere._isa_atmo_functions import (
     pressure_isa,
     temperature_isa,
-    isa_base_altitude,
 )
 
 # Define the altitudes of knot points

aerosandbox/atmosphere/atmosphere.py

@@ -86,7 +86,7 @@ def get_item_of_attribute(a):
                 else:
                     try:
                         return a[index]
-                    except IndexError as e:
+                    except IndexError:
                         raise IndexError(
                             f"A state variable could not be indexed; it has length {len(a)} while the"
                             f"parent has length {l}."
@@ -114,7 +114,7 @@ def __len__(self):
                 try:
                     v[0]
                     length = 1
-                except (TypeError, IndexError, KeyError) as e:
+                except (TypeError, IndexError, KeyError):
                     pass
             elif length == 0 or length == 1:
                 length = np.length(v)
@@ -318,7 +318,7 @@ def knudsen(self, length):
         a.set_ylim(altitude.min() / u.foot, altitude.max() / u.foot)
     ax[0].set_ylabel("Altitude [ft]")
     plt.legend(title="Method")
-    p.show_plot(f"Atmosphere", rotate_axis_labels=False, legend=False)
+    p.show_plot("Atmosphere", rotate_axis_labels=False, legend=False)
 
     fig, ax = plt.subplots(1, 2, sharey=True)
     ax[0].plot(

aerosandbox/atmosphere/thermodynamics/choked_flow.py

@@ -1,4 +1,3 @@
-import aerosandbox.numpy as np
 from aerosandbox.atmosphere.thermodynamics.gas import universal_gas_constant
 
 

aerosandbox/atmosphere/thermodynamics/gas.py

@@ -1,6 +1,5 @@
 import aerosandbox.numpy as np
 from aerosandbox.tools.string_formatting import eng_string
-import copy
 from typing import Union
 
 universal_gas_constant = 8.31432  # J/(mol*K); universal gas constant

aerosandbox/dynamics/point_mass/common_point_mass.py

@@ -1,6 +1,6 @@
 import aerosandbox.numpy as np
 from aerosandbox.common import AeroSandboxObject
-from abc import ABC, abstractmethod, abstractproperty
+from abc import ABC, abstractmethod
 from typing import Union, Dict, Tuple, List
 from aerosandbox import (
     MassProperties,
@@ -211,7 +211,7 @@ def get_item_of_attribute(a):
                 else:
                     try:
                         return a[index]
-                    except IndexError as e:
+                    except IndexError:
                         raise IndexError(
                             f"A state variable could not be indexed; it has length {len(a)} while the"
                             f"parent has length {l}."

aerosandbox/dynamics/point_mass/point_1D/horizontal.py

@@ -3,7 +3,7 @@
 )
 from aerosandbox.weights.mass_properties import MassProperties
 import aerosandbox.numpy as np
-from typing import Union, Dict, Tuple
+from typing import Union, Dict
 
 
 class DynamicsPointMass1DHorizontal(DynamicsPointMass3DCartesian):

aerosandbox/dynamics/point_mass/point_1D/vertical.py

@@ -3,7 +3,7 @@
 )
 from aerosandbox.weights.mass_properties import MassProperties
 import aerosandbox.numpy as np
-from typing import Union, Dict, Tuple
+from typing import Union, Dict
 
 
 class DynamicsPointMass1DVertical(DynamicsPointMass3DCartesian):

aerosandbox/dynamics/point_mass/point_2D/cartesian.py

@@ -3,7 +3,7 @@
 )
 from aerosandbox.weights.mass_properties import MassProperties
 import aerosandbox.numpy as np
-from typing import Union, Dict, Tuple
+from typing import Union, Dict
 
 
 class DynamicsPointMass2DCartesian(DynamicsPointMass3DCartesian):

aerosandbox/dynamics/point_mass/point_2D/speed_gamma.py

@@ -3,7 +3,7 @@
 )
 from aerosandbox.weights.mass_properties import MassProperties
 import aerosandbox.numpy as np
-from typing import Union, Dict, Tuple
+from typing import Union, Dict
 
 
 class DynamicsPointMass2DSpeedGamma(DynamicsPointMass3DSpeedGammaTrack):

aerosandbox/dynamics/rigid_body/common_rigid_body.py

@@ -2,8 +2,8 @@
 from aerosandbox.dynamics.point_mass.common_point_mass import (
     _DynamicsPointMassBaseClass,
 )
-from abc import ABC, abstractmethod, abstractproperty
-from typing import Union, Tuple
+from abc import ABC, abstractmethod
+from typing import Union
 from aerosandbox import OperatingPoint, Atmosphere