config_template.cfg

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%                                                                              %
% SU2 configuration file                                                       %
% Case description: _________________________________________________________  %
% Author: ___________________________________________________________________  %
% Institution: ______________________________________________________________  %
% Date: __________                                                             %
% File Version 3.1.0 "eagle"                                                   %
%                                                                              %
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% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
% Physical governing equations (EULER, NAVIER_STOKES,
%                               TNE2_EULER, TNE2_NAVIER_STOKES,
%                               WAVE_EQUATION, HEAT_EQUATION, LINEAR_ELASTICITY,
%                               POISSON_EQUATION)
PHYSICAL_PROBLEM= EULER
%
% Specify turbulence model (NONE, SA, SST)
KIND_TURB_MODEL= NONE
%
% Mathematical problem (DIRECT, ADJOINT, LINEARIZED)
MATH_PROBLEM= DIRECT
%
% Restart solution (NO, YES)
RESTART_SOL= NO
%
% Regime type (COMPRESSIBLE, INCOMPRESSIBLE, FREESURFACE)
REGIME_TYPE= COMPRESSIBLE
%
% Gravity force, only incompressible (NO, YES)
GRAVITY_FORCE= NO
%
% Axisymmetric simulation, only compressible (NO, YES)
AXISYMMETRIC= NO
%
% Perform a low fidelity simulation (NO, YES)
LOW_FIDELITY_SIMULATION= NO

% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
%
% Mach number (non-dimensional, based on the free-stream values)
MACH_NUMBER= 0.8
%
% Angle of attack (degrees, only for compressible flows)
AoA= 1.25
%
% Side-slip angle (degrees, only for compressible flows)
SIDESLIP_ANGLE= 0.0
%
% Free-stream pressure (101325.0 N/m^2 by default)  
FREESTREAM_PRESSURE= 101325.0
%
% Free-stream temperature (273.15 K by default)
FREESTREAM_TEMPERATURE= 273.15
%
% Reynolds number (non-dimensional, based on the free-stream values)
REYNOLDS_NUMBER= 6.5E6
%
% Reynolds length (1 m by default)
REYNOLDS_LENGTH= 1.0

% -------------------- INCOMPRESSIBLE FREE-STREAM DEFINITION ------------------%
%
% Free-stream density (1.2886 Kg/m^3 (air), 998.2 Kg/m^3 (water))
FREESTREAM_DENSITY= 998.2
%
% Free-stream velocity (m/s)
FREESTREAM_VELOCITY= ( 5.0, 0.00, 0.00 )
%
% Free-stream viscosity (1.853E-5 Ns/m^2 (air), 0.798E-3 Ns/m^2 (water))
FREESTREAM_VISCOSITY= 1.002E-3

% -------------- COMPRESSIBLE AND INCOMPRESSIBLE FLUID CONSTANTS --------------%
%
% Ratio of specific heats (1.4 (air), only for compressible flows)
GAMMA_VALUE= 1.4
%
% Specific gas constant (287.87 J/kg*K (air), only for compressible flows)
GAS_CONSTANT= 287.87
%
% Laminar Prandtl number (0.72 (air), only for compressible flows)
PRANDTL_LAM= 0.72
%
% Turbulent Prandtl number (0.9 (air), only for compressible flows)
PRANDTL_TURB= 0.9
%
% Value of the Bulk Modulus (1.42E5 N/m^2 (air), 2.2E9 N/m^2 (water),
%                            only for incompressible flows) 
BULK_MODULUS= 1.42E5
%
% Artifical compressibility factor (1.0 by default,
%                                   only for incompressible flows) 
ARTCOMP_FACTOR= 1.0

% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
%
% Reference origin for moment computation
REF_ORIGIN_MOMENT_X = 0.25
REF_ORIGIN_MOMENT_Y = 0.00
REF_ORIGIN_MOMENT_Z = 0.00
%
% Reference length for pitching, rolling, and yawing non-dimensional moment
REF_LENGTH_MOMENT= 1.0
%
% Reference area for force coefficients (0 implies automatic calculation)
REF_AREA= 1.0
%
% Reference pressure (1.0 N/m^2 by default, only for compressible flows)
REF_PRESSURE= 1.0
%
% Reference temperature (1.0 K by default, only for compressible flows)
REF_TEMPERATURE= 1.0
%
% Reference density (1.0 Kg/m^3 by default, only for compressible flows)
REF_DENSITY= 1.0

% ------------------------- UNSTEADY SIMULATION -------------------------------%
%
% Unsteady simulation (NO, TIME_STEPPING, DUAL_TIME_STEPPING-1ST_ORDER, 
%                      DUAL_TIME_STEPPING-2ND_ORDER, TIME_SPECTRAL)
UNSTEADY_SIMULATION= NO
%
% Time Step for dual time stepping simulations (s)
UNST_TIMESTEP= 0.0
%
% Total Physical Time for dual time stepping simulations (s)
UNST_TIME= 50.0
%
% Unsteady Courant-Friedrichs-Lewy number of the finest grid
UNST_CFL_NUMBER= 0.0
%
% Number of internal iterations (dual time method)
UNST_INT_ITER= 200
%
% Integer number of periodic time instances for Time Spectral
TIME_INSTANCES= 1

% ----------------------- DYNAMIC MESH DEFINITION -----------------------------%
%
% Dynamic mesh simulation (NO, YES)
GRID_MOVEMENT= NO
%
% Type of dynamic mesh (NONE, RIGID_MOTION, DEFORMING, ROTATING_FRAME,
%                       MOVING_WALL, FLUID_STRUCTURE, AEROELASTIC, ELASTICITY,
%                       EXTERNAL, AEROELASTIC_RIGID_MOTION)
GRID_MOVEMENT_KIND= DEFORMING
%
% Motion mach number (non-dimensional). Used for initializing a viscous flow
% with the Reynolds number and for computing force coeffs. with dynamic meshes.
MACH_MOTION= 0.8
%
% Moving wall boundary marker(s) (NONE = no marker, ignored for RIGID_MOTION)
MARKER_MOVING= ( airfoil )
%
% Coordinates of the motion origin
MOTION_ORIGIN_X= 0.25
MOTION_ORIGIN_Y= 0.0
MOTION_ORIGIN_Z= 0.0
%
% Angular velocity vector (rad/s) about the motion origin
ROTATION_RATE_X = 0.0
ROTATION_RATE_Y = 0.0
ROTATION_RATE_Z = 0.0
%
% Pitching angular freq. (rad/s) about the motion origin
PITCHING_OMEGA_X= 0.0 
PITCHING_OMEGA_Y= 0.0
PITCHING_OMEGA_Z= 106.69842
%
% Pitching amplitude (degrees) about the motion origin
PITCHING_AMPL_X= 0.0
PITCHING_AMPL_Y= 0.0
PITCHING_AMPL_Z= 1.01
%
% Pitching phase offset (degrees) about the motion origin
PITCHING_PHASE_X= 0.0
PITCHING_PHASE_Y= 0.0
PITCHING_PHASE_Z= 0.0
%
% Translational velocity (m/s) in the x, y, & z directions
TRANSLATION_RATE_X = 0.0
TRANSLATION_RATE_Y = 0.0
TRANSLATION_RATE_Z = 0.0
%
% Plunging angular freq. (rad/s) in x, y, & z directions
PLUNGING_OMEGA_X= 0.0
PLUNGING_OMEGA_Y= 0.0
PLUNGING_OMEGA_Z= 0.0
%
% Plunging amplitude (m) in x, y, & z directions
PLUNGING_AMPL_X= 0.0
PLUNGING_AMPL_Y= 0.0
PLUNGING_AMPL_Z= 0.0
%
% Move Motion Origin for marker moving (1 or 0)
MOVE_MOTION_ORIGIN = 0

% --------------------------- GUST SIMULATION ---------------------------------%
% The gust simulation requires the GRID_MOVEMENT flag to be set to YES.
%
% Apply a wind gust (YES, NO)
WIND_GUST = NO
%
% Type of gust (NONE,TOP_HAT,SINE,ONE_M_COSINE,VORTEX,EOG)
GUST_TYPE = NONE
%
% Direction of the gust (X_DIR or Y_DIR)
GUST_DIR = Y_DIR
%
% Gust wavelenght (meters)
GUST_WAVELENGTH= 10.0
%
% Number of gust periods
GUST_PERIODS= 1.0
%
% Gust amplitude (m/s)
GUST_AMPL= 10.0
%
% Time at which to begin the gust (sec)
GUST_BEGIN_TIME= 0.0
%
% Location at which the gust begins (meters) */
GUST_BEGIN_LOC= 0.0

% ---------------------------- FREE SURFACE SIMULATION ------------------------%
%
% Ratio of density for two phase problems
RATIO_DENSITY= 0.00129
%
% Ratio of viscosity for two phase problems
RATIO_VISCOSITY= 0.001
%
% Location of the freesurface (y or z coordinate)
FREESURFACE_ZERO= 0.0
%
% Thickness of the interface in a free surface problem
FREESURFACE_THICKNESS= 0.1
%
% Free surface damping coefficient
FREESURFACE_DAMPING_COEFF= 0.00
%
% Free surface damping length (times the baseline wave)
FREESURFACE_DAMPING_LENGTH= 1.0
%
% Location of the free surface outlet surface (x or y coordinate)
FREESURFACE_OUTLET= 12.0
%
% Free surface depth surface (x or y coordinate)
FREESURFACE_DEPTH= 0.500

% ------------------------ SUPERSONIC SIMULATION ------------------------------%
%
% Evaluate equivalent area on the Near-Field (NO, YES)
EQUIV_AREA= NO
%
% Integration limits of the equivalent area ( xmin, xmax, Dist_NearField )
EA_INT_LIMIT= ( 1.6, 2.9, 1.0 )
%
% Fix an azimuthal line due to misalignments of the near-field
FIX_AZIMUTHAL_LINE= 90.0
%
% Value of the viscous drag for inviscid simulation and design
CTE_VISCOUS_DRAG= 0.0
%
% Subsonic region around engine inlet.
SUBSONIC_NACELLE_INFLOW = NO
%
% Damping factor for the engine inlet.
DAMP_NACELLE_INFLOW= 0.1
%
% Drag weight in sonic boom Objective Function (from 0.0 to 1.0)
DRAG_IN_SONICBOOM= 0.5

% --------------------- INVERSE DESIGN SIMULATION -----------------------------%
%
% Evaluate an inverse design problem using Cp (NO, YES)
INV_DESIGN_CP= NO
%
% Evaluate an inverse design problem using heat flux (NO, YES)
INV_DESIGN_HEATFLUX= NO

% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
%
% Euler wall boundary marker(s) (NONE = no marker)
MARKER_EULER= ( airfoil )
%
% Navier-Stokes (no-slip), constant heat flux wall  marker(s) (NONE = no marker)
% Format: ( marker name, constant heat flux (J/m^2), ... )
MARKER_HEATFLUX= ( NONE )
%
% Navier-Stokes (no-slip), isothermal wall marker(s) (NONE = no marker)
% Format: ( marker name, constant wall temperature (K), ... )
MARKER_ISOTHERMAL= ( NONE )
%
% Far-field boundary marker(s) (NONE = no marker)
MARKER_FAR= ( farfield )
%
% Symmetry boundary marker(s) (NONE = no marker)
MARKER_SYM= ( NONE )
%
% Near-Field boundary marker(s) (NONE = no marker)
MARKER_NEARFIELD= ( NONE )
%
% Zone interface boundary marker(s) (NONE = no marker)
MARKER_INTERFACE= ( NONE )
%
% Inlet boundary type (TOTAL_CONDITIONS, MASS_FLOW)
INLET_TYPE= TOTAL_CONDITIONS
%
% Inlet boundary marker(s) with the following formats (NONE = no marker) 
% Total Conditions: (inlet marker, total temp, total pressure, flow_direction_x, 
%           flow_direction_y, flow_direction_z, ... ) where flow_direction is
%           a unit vector.
% Mass Flow: (inlet marker, density, velocity magnitude, flow_direction_x, 
%           flow_direction_y, flow_direction_z, ... ) where flow_direction is
%           a unit vector.
MARKER_INLET= ( NONE )
%
% Supersonic inlet boundary marker(s) (NONE = no marker) 
% Format: (inlet marker, temperature, static pressure, velocity_x, 
%           velocity_y, velocity_z, ... ), i.e. primitive variables specified.
MARKER_SUPERSONIC_INLET= ( NONE )
%
% Outlet boundary marker(s) (NONE = no marker)
% Format: ( outlet marker, back pressure (static), ... )
MARKER_OUTLET= ( NONE )
%
% Periodic boundary marker(s) (NONE = no marker)
% Format: ( periodic marker, donor marker, rotation_center_x, rotation_center_y, 
% rotation_center_z, rotation_angle_x-axis, rotation_angle_y-axis, 
% rotation_angle_z-axis, translation_x, translation_y, translation_z, ... )
MARKER_PERIODIC= ( NONE )
%
% Nacelle inflow boundary marker(s) (NONE = no marker)
% Format: ( nacelle inflow marker, fan face Mach, ... )
MARKER_NACELLE_INFLOW= ( NONE )
%
% Nacelle exhaust boundary marker(s) with the following formats (NONE = no marker) 
% Format: (nacelle exhaust marker, total nozzle temp, total nozzle pressure, ... ) 
MARKER_NACELLE_EXHAUST= ( NONE )
%
% Displacement boundary marker(s) (NONE = no marker)
% Format: ( displacement marker, displacement value normal to the surface, ... )
MARKER_NORMAL_DISPL= ( NONE )
%
% Load boundary marker(s) (NONE = no marker)
% Format: ( load marker, force value normal to the surface, ... )
MARKER_NORMAL_LOAD= ( NONE )
%
% Pressure boundary marker(s) (NONE = no marker)
% Format: ( pressure marker )
MARKER_PRESSURE= ( NONE )
%
% Neumann bounday marker(s) (NONE = no marker)
MARKER_NEUMANN= ( Wall_Adiabatic )
%
% Dirichlet boundary marker(s) (NONE = no marker)
MARKER_DIRICHLET= ( Wall_Isothermal, Outflow )

% ------------------------ SURFACES IDENTIFICATION ----------------------------%
%
% Marker(s) of the surface in the surface flow solution file
MARKER_PLOTTING = ( airfoil )
%
% Marker(s) of the surface where the non-dimensional coefficients are evaluated.
MARKER_MONITORING = ( airfoil )
%
% Marker(s) of the surface where obj. func. (design problem) will be evaluated
MARKER_DESIGNING = ( airfoil )

% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
%
% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
NUM_METHOD_GRAD= GREEN_GAUSS
%
% Objective function in optimization problem (DRAG, LIFT, SIDEFORCE, MOMENT_X,
%                                             MOMENT_Y, MOMENT_Z, EFFICIENCY,
%                                             EQUIVALENT_AREA, NEARFIELD_PRESSURE,
%                                             FORCE_X, FORCE_Y, FORCE_Z, THRUST,
%                                             TORQUE, FREE_SURFACE, TOTAL_HEATFLUX,
%                                             MAXIMUM_HEATFLUX, INVERSE_DESIGN_PRESSURE,
%                                             INVERSE_DESIGN_HEATFLUX)
OBJECTIVE_FUNCTION= DRAG
%
% Courant-Friedrichs-Lewy condition of the finest grid
CFL_NUMBER= 10.0
%
% CFL ramp (factor, number of iterations, CFL limit)
CFL_RAMP= ( 1.05, 50, 2.0 )
%
% Number of total iterations
EXT_ITER= 999999
%
% Runge-Kutta alpha coefficients
RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )

% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
%
% Reference element length for computing the slope and sharp edges limiters.
REF_ELEM_LENGTH= 0.1
%
% Coefficient for the limiter
LIMITER_COEFF= 0.3
%
% Coefficient for the sharp edges limiter
SHARP_EDGES_COEFF= 3.0
%
% Reference coefficient (sensitivity) for detecting sharp edges.
REF_SHARP_EDGES= 3.0
%
% Remove sharp edges from the sensitivity evaluation (NO, YES)
SENS_REMOVE_SHARP= NO

% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
%
% Linear solver for implicit formulations (BCGSTAB, FGMRES)
LINEAR_SOLVER= FGMRES
%
% Preconditioner of the Krylov linear solver (JACOBI, LINELET, LU_SGS)
LINEAR_SOLVER_PREC= LU_SGS
%
% Minimum error of the linear solver for implicit formulations
LINEAR_SOLVER_ERROR= 1E-4
%
% Max number of iterations of the linear solver for the implicit formulation
LINEAR_SOLVER_ITER= 5
%
% Relaxation coefficient
LINEAR_SOLVER_RELAX= 1.0

% -------------------------- MULTIGRID PARAMETERS -----------------------------%
%
% Multi-grid Levels (0 = no multi-grid)
MGLEVEL= 2 
%
% Multi-grid Cycle (0 = V cycle, 1 = W Cycle)
MGCYCLE= 0
%
% CFL reduction factor on the coarse levels
MG_CFL_REDUCTION= 0.8
%
% Maximum number of children in the agglomeration stage
MAX_CHILDREN= 50
%
% Maximum length of an agglomerated element (relative to the domain)
MAX_DIMENSION= 0.1
%
% Multi-grid pre-smoothing level
MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
%
% Multi-grid post-smoothing level
MG_POST_SMOOTH= ( 0, 0, 0, 0 )
%
% Jacobi implicit smoothing of the correction
MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )
%
% Damping factor for the residual restriction
MG_DAMP_RESTRICTION= 0.85
%
% Damping factor for the correction prolongation
MG_DAMP_PROLONGATION= 0.85

% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
%                              TURKEL_PREC, MSW)
CONV_NUM_METHOD_FLOW= JST
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
%
SPATIAL_ORDER_FLOW= 2ND_ORDER_LIMITER
%
% Slope limiter (VENKATAKRISHNAN, MINMOD)
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
%
% 1st, 2nd and 4th order artificial dissipation coefficients
AD_COEFF_FLOW= ( 0.15, 0.5, 0.02 )
%
% Viscous numerical method (AVG_GRAD, AVG_GRAD_CORRECTED, GALERKIN)
VISC_NUM_METHOD_FLOW= AVG_GRAD_CORRECTED
%
% Source term numerical method (PIECEWISE_CONSTANT)
SOUR_NUM_METHOD_FLOW= PIECEWISE_CONSTANT
%
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
TIME_DISCRE_FLOW= EULER_IMPLICIT

% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
%
% Convective numerical method (SCALAR_UPWIND)
CONV_NUM_METHOD_TURB= SCALAR_UPWIND
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
%
SPATIAL_ORDER_TURB= 1ST_ORDER
%
% Slope limiter (VENKATAKRISHNAN, MINMOD)
SLOPE_LIMITER_TURB= VENKATAKRISHNAN
%
% Viscous numerical method (AVG_GRAD, AVG_GRAD_CORRECTED)
VISC_NUM_METHOD_TURB= AVG_GRAD_CORRECTED
%
% Source term numerical method (PIECEWISE_CONSTANT)
SOUR_NUM_METHOD_TURB= PIECEWISE_CONSTANT
%
% Time discretization (EULER_IMPLICIT)
TIME_DISCRE_TURB= EULER_IMPLICIT
%
% Reduction factor of the CFL coefficient in the turbulence problem
CFL_REDUCTION_TURB= 1.0

% -------------------- TNE2 NUMERICAL METHOD DEFINITION -----------------------%
%
% Convective numerical method (ROE, AUSM, MSW)
CONV_NUM_METHOD_TNE2= MSW
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
%
SPATIAL_ORDER_TNE2= 1ST_ORDER
%
% Slope limiter (VENKATAKRISHNAN)
SLOPE_LIMITER_TNE2= VENKATAKRISHNAN
%
% Viscous numerical method (AVG_GRAD, AVG_GRAD_CORRECTED, GALERKIN)
VISC_NUM_METHOD_TNE2= AVG_GRAD_CORRECTED
%
% Source term numerical method (PIECEWISE_CONSTANT)
SOUR_NUM_METHOD_TNE2= PIECEWISE_CONSTANT
%
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
TIME_DISCRE_TNE2= EULER_IMPLICIT

% --------------------- HEAT NUMERICAL METHOD DEFINITION ----------------------%
%
% Value of the thermal diffusivity
THERMAL_DIFFUSIVITY= 1.0
%
% Viscous numerical method (GALERKIN)
VISC_NUM_METHOD_HEAT= GALERKIN
%
% Source term numerical method (PIECEWISE_CONSTANT)
SOUR_NUM_METHOD_HEAT= PIECEWISE_CONSTANT

% --------------- POISSON POTENTIAL NUMERICAL METHOD DEFINITION ---------------%
%
% Viscous numerical method (GALERKIN)
VISC_NUM_METHOD_POISSON= GALERKIN
%
% Source term numerical method (PIECEWISE_CONSTANT)
SOUR_NUM_METHOD_POISSON= PIECEWISE_CONSTANT

% ---------------- ADJOINT-FLOW NUMERICAL METHOD DEFINITION -------------------%
%
% Convective numerical method (JST, LAX-FRIEDRICH, ROE)
CONV_NUM_METHOD_ADJFLOW= JST
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
%
SPATIAL_ORDER_ADJFLOW= 2ND_ORDER
%
% Slope limiter (VENKATAKRISHNAN, SHARP_EDGES)
SLOPE_LIMITER_ADJFLOW= VENKATAKRISHNAN
%
% 1st, 2nd, and 4th order artificial dissipation coefficients
AD_COEFF_ADJFLOW= ( 0.15, 0.5, 0.02 )
%
% Viscous numerical method (AVG_GRAD, AVG_GRAD_CORRECTED, GALERKIN)
VISC_NUM_METHOD_ADJFLOW= AVG_GRAD_CORRECTED
%
% Source term numerical method (PIECEWISE_CONSTANT)
SOUR_NUM_METHOD_ADJFLOW= PIECEWISE_CONSTANT
%
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT)
TIME_DISCRE_ADJFLOW= EULER_IMPLICIT
%
% Reduction factor of the CFL coefficient in the adjoint problem
CFL_REDUCTION_ADJFLOW= 0.8
%
% Limit value for the adjoint variable
LIMIT_ADJFLOW= 1E6

% ---------------- ADJOINT-TURBULENT NUMERICAL METHOD DEFINITION --------------%
%
% Convective numerical method (SCALAR_UPWIND)
CONV_NUM_METHOD_ADJTURB= SCALAR_UPWIND
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
%
SPATIAL_ORDER_ADJTURB= 1ST_ORDER
%
% Slope limiter (VENKATAKRISHNAN)
SLOPE_LIMITER_ADJTURB= VENKATAKRISHNAN
%
% Viscous numerical method (AVG_GRAD, AVG_GRAD_CORRECTED)
VISC_NUM_METHOD_ADJTURB= AVG_GRAD_CORRECTED
%
% Source term numerical method (PIECEWISE_CONSTANT)
SOUR_NUM_METHOD_ADJTURB= PIECEWISE_CONSTANT
%
% Time discretization (EULER_IMPLICIT)
TIME_DISCRE_ADJTURB= EULER_IMPLICIT
%
% Reduction factor of the CFL coefficient in the adjoint turbulent problem
CFL_REDUCTION_ADJTURB= 0.01

% ---------------- ADJOINT-TNE2 NUMERICAL METHOD DEFINITION -------------------%
%
% Convective numerical method (LAX-FRIEDRICH)
CONV_NUM_METHOD_ADJTNE2= LAX-FRIEDRICH
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
%
SPATIAL_ORDER_ADJTNE2= 1ST_ORDER
%
% Slope limiter (VENKATAKRISHNAN)
SLOPE_LIMITER_ADJTNE2= VENKATAKRISHNAN
%
% 1st, 2nd, and 4th order artificial dissipation coefficients
AD_COEFF_ADJTNE2= ( 0.15, 0.0, 0.02 )
%
% Viscous numerical method (AVG_GRAD, AVG_GRAD_CORRECTED, GALERKIN)
VISC_NUM_METHOD_ADJTNE2= AVG_GRAD
%
% Source term numerical method (PIECEWISE_CONSTANT)
SOUR_NUM_METHOD_ADJTNE2= PIECEWISE_CONSTANT
%
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT)
TIME_DISCRE_ADJTNE2= EULER_IMPLICIT

% --------------- ADJOINT-FREE SURFACE NUMERICAL METHOD DEFINITION ------------%
%
% Convective numerical method (SCALAR_UPWIND)
CONV_NUM_METHOD_ADJLEVELSET= SCALAR_UPWIND
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
%
SPATIAL_ORDER_ADJLEVELSET= 2ND_ORDER
%
% Slope limiter (VENKATAKRISHNAN)
SLOPE_LIMITER_ADJLEVELSET= VENKATAKRISHNAN
%
% Source term numerical method (PIECEWISE_CONSTANT)
SOUR_NUM_METHOD_ADJLEVELSET= PIECEWISE_CONSTANT
%
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
TIME_DISCRE_ADJLEVELSET= EULER_IMPLICIT

% --------------------------- PARTITIONING STRATEGY ---------------------------%
%
% Write a tecplot file for each partition (NO, YES)
VISUALIZE_PART= NO

% ----------------------- GEOMETRY EVALUATION PARAMETERS ----------------------%
%
% Geometrical evaluation mode (FUNCTION, GRADIENT)
GEO_MODE= FUNCTION
%
% Marker(s) of the surface where geometrical based func. will be evaluated
GEO_MARKER= ( airfoil )
%
% Number of airfoil sections
GEO_NUMBER_SECTIONS= 5
%
% Orientation of airfoil sections (X_AXIS, Y_AXIS, Z_AXIS)
GEO_ORIENTATION_SECTIONS= Y_AXIS
%
% Location (coordinate) of the airfoil sections (MinValue, MaxValue)
GEO_LOCATION_SECTIONS= (1.5, 3.5)
%
% Plot loads and Cp distributions on each airfoil section
GEO_PLOT_SECTIONS= NO
%
% Number of section cuts to make when calculating internal volume
GEO_VOLUME_SECTIONS= 101

% ------------------------- GRID ADAPTATION STRATEGY --------------------------%
%
% Percentage of new elements (% of the original number of elements)
NEW_ELEMS= 5
%
% Kind of grid adaptation (NONE, FULL, FULL_FLOW, GRAD_FLOW, FULL_ADJOINT,
%                          GRAD_ADJOINT, GRAD_FLOW_ADJ, ROBUST,
%                          FULL_LINEAR, COMPUTABLE, COMPUTABLE_ROBUST,
%                          REMAINING, WAKE, SMOOTHING, SUPERSONIC_SHOCK, 
%                          TWOPHASE)
KIND_ADAPT= FULL_FLOW
%
% Scale factor for the dual volume
DUALVOL_POWER= 0.5
%
% Adapt the boundary elements (NO, YES)
ADAPT_BOUNDARY= YES

% ----------------------- DESIGN VARIABLE PARAMETERS --------------------------%
%
% Kind of deformation (FFD_SETTING, FFD_CONTROL_POINT_2D, FFD_CAMBER_2D, FFD_THICKNESS_2D,
%                      HICKS_HENNE, COSINE_BUMP, PARABOLIC,
%                      NACA_4DIGITS, DISPLACEMENT, ROTATION, FFD_CONTROL_POINT, 
%                      FFD_DIHEDRAL_ANGLE, FFD_TWIST_ANGLE, FFD_ROTATION,
%                      FFD_CAMBER, FFD_THICKNESS, SURFACE_FILE, AIRFOIL)
DV_KIND= FFD_SETTING 
%
% Marker of the surface in which we are going apply the shape deformation
DV_MARKER= ( airfoil )
%
% Parameters of the shape deformation
% - FFD_CONTROL_POINT_2D ( FFD_Box_ID, i_Ind, j_Ind, x_Disp, y_Disp )
% - FFD_CAMBER_2D ( FFD_Box_ID, i_Ind )
% - FFD_THICKNESS_2D ( FFD_Box_ID, i_Ind )
% - HICKS_HENNE ( Lower Surface (0)/Upper Surface (1)/Only one Surface (2), x_Loc )
% - COSINE_BUMP ( Lower Surface (0)/Upper Surface (1)/Only one Surface (2), x_Loc, x_Size )
% - FOURIER ( Lower Surface (0)/Upper Surface (1)/Only one Surface (2), index, cos(0)/sin(1) )
% - SPHERICAL ( ControlPoint_Index, Theta_Disp, R_Disp )
% - NACA_4DIGITS ( 1st digit, 2nd digit, 3rd and 4th digit )
% - PARABOLIC ( Center, Thickness )
% - DISPLACEMENT ( x_Disp, y_Disp, z_Disp )
% - ROTATION ( x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% - OBSTACLE ( Center, Bump size )
% - FFD_CONTROL_POINT ( FFD_Box_ID, i_Ind, j_Ind, k_Ind, x_Disp, y_Disp, z_Disp )
% - FFD_DIHEDRAL_ANGLE ( FFD_Box_ID, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% - FFD_TWIST_ANGLE ( FFD_Box_ID, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% - FFD_ROTATION ( FFD_Box_ID, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% - FFD_CAMBER ( FFD_Box_ID, i_Ind, j_Ind )
% - FFD_THICKNESS ( FFD_Box_ID, i_Ind, j_Ind )
DV_PARAM= ( 1, 0.5 )
%
% Value of the shape deformation
DV_VALUE= 0.01
%
% Surface deformation input filename (SURFACE_FILE DV only)
MOTION_FILENAME= mesh_motion.dat

% ------------------------ GRID DEFORMATION PARAMETERS ------------------------%
%
% Number of smoothing iterations for FEA mesh deformation
DEFORM_LINEAR_ITER= 500
%
% Number of nonlinear deformation iterations (surface deformation increments)
DEFORM_NONLINEAR_ITER= 1
%
% Print the residuals during mesh deformation to the console (YES, NO)
DEFORM_CONSOLE_OUTPUT= YES
%
% Factor to multiply smallest cell volume for deform tolerance (0.001 default)
DEFORM_TOL_FACTOR = 0.001
%
% Type of element stiffness imposed for FEA mesh deformation (INVERSE_VOLUME, 
%                                          WALL_DISTANCE, CONSTANT_STIFFNESS)
DEFORM_STIFFNESS_TYPE= INVERSE_VOLUME
%
% Visualize the deformation (NO, YES)
VISUALIZE_DEFORMATION= NO
%
% Divide elements into triangles and tetrahedra (NO, YES)
DIVIDE_ELEMENTS= NO
%
% Hold the grid fixed in a region (NO, YES)
HOLD_GRID_FIXED= NO
%
% Coordinates of the box where the grid will be deformed (Xmin, Ymin, Zmin, 
%                                                         Xmax, Ymax, Zmax)
HOLD_GRID_FIXED_COORD= ( -0.5, -0.49, 0.0, 2.5, 0.49, 0.0 )

% -------------------- FREE-FORM DEFORMATION PARAMETERS -----------------------%
%
% Tolerance of the Free-Form Deformation point inversion
FFD_TOLERANCE= 1E-8
%
% Maximum number of iterations in the Free-Form Deformation point inversion
FFD_ITERATIONS= 1000

% --------------------------- CONVERGENCE PARAMETERS --------------------------%
%
% Convergence criteria (CAUCHY, RESIDUAL)
%
CONV_CRITERIA= RESIDUAL
%
% Residual reduction (order of magnitude with respect to the initial value)
RESIDUAL_REDUCTION= 5
%
% Min value of the residual (log10 of the residual)
RESIDUAL_MINVAL= -8
%
% Start convergence criteria at iteration number
STARTCONV_ITER= 10
%
% Number of elements to apply the criteria
CAUCHY_ELEMS= 100
%
% Epsilon to control the series convergence
CAUCHY_EPS= 1E-10
%
% Direct function to apply the convergence criteria (LIFT, DRAG, NEARFIELD_PRESS)
CAUCHY_FUNC_FLOW= DRAG
%
% Adjoint function to apply the convergence criteria (SENS_GEOMETRY, SENS_MACH)
CAUCHY_FUNC_ADJFLOW= SENS_GEOMETRY

% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
%
% Mesh input file
MESH_FILENAME= mesh_NACA0012_inv.su2
%
% Mesh input file format (SU2, CGNS, NETCDF_ASCII)
MESH_FORMAT= SU2
%
% Convert a CGNS mesh to SU2 format (YES, NO)
CGNS_TO_SU2= NO
%
% Change the scale of the numerical grid (useful to change the length units
%                                         or to re-scale the grid)
MESH_SCALE_CHANGE= 1.0
%
% Write a new mesh after reading only in serial (NO, YES)
MESH_OUTPUT= NO
%
% Mesh output file
MESH_OUT_FILENAME= mesh_out.su2
%
% Restart flow input file
SOLUTION_FLOW_FILENAME= solution_flow.dat
%
% Restart linear flow input file
SOLUTION_LIN_FILENAME= solution_lin.dat
%
% Restart adjoint input file
SOLUTION_ADJ_FILENAME= solution_adj.dat
%
% Output file format (TECPLOT, CGNS, PARAVIEW, TECPLOT_BINARY)
OUTPUT_FORMAT= TECPLOT
%
% Output file convergence history (w/o extension) 
CONV_FILENAME= history
%
% Output file restart flow
RESTART_FLOW_FILENAME= restart_flow.dat
%
% Output file restart adjoint
RESTART_ADJ_FILENAME= restart_adj.dat
%
% Output file linear flow
RESTART_LIN_FILENAME= restart_lin.dat
%
% Output file flow (w/o extension) variables
VOLUME_FLOW_FILENAME= flow
%
% Output file adjoint (w/o extension) variables
VOLUME_ADJ_FILENAME= adjoint
%
% Output file linearized (w/o extension) variables
VOLUME_LIN_FILENAME= linearized
%
% Output Objective function
OBJFUNC_FILENAME= of_eval.dat
%
% Output objective function gradient (using continuous adjoint)
GRAD_OBJFUNC_FILENAME= of_grad.dat
%
% Output file surface flow coefficient (w/o extension)
SURFACE_FLOW_FILENAME= surface_flow
%
% Output file surface adjoint coefficient (w/o extension)
SURFACE_ADJ_FILENAME= surface_adjoint
%
% Output file surface linear coefficient (w/o extension)
SURFACE_LIN_FILENAME= surface_linear
%
% Writing solution file frequency
WRT_SOL_FREQ= 1000
%
% Writing solution file frequency for physical time steps (dual time)
WRT_SOL_FREQ_DUALTIME= 1
%
% Writing convergence history frequency
WRT_CON_FREQ= 1
%
% Writing convergence history frequency (dual time, only written to screen)
WRT_CON_FREQ_DUALTIME= 10
%
% Output residual values in the solution files
WRT_RESIDUALS= NO

% --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------%
% Available flow based objective functions or constraint functions
%    DRAG, LIFT, SIDEFORCE, EFFICIENCY,
%    FORCE_X, FORCE_Y, FORCE_Z,
%    MOMENT_X, MOMENT_Y, MOMENT_Z,
%    THRUST, TORQUE, FIGURE_OF_MERIT,
%    EQUIVALENT_AREA, NEARFIELD_PRESSURE, 
%    TOTAL_HEATFLUX, MAXIMUM_HEATFLUX,
%    INVERSE_DESIGN_PRESSURE, INVERSE_DESIGN_HEATFLUX,
%    FREE_SURFACE
%
% Available geometrical based objective functions or constraint functions
%    MAX_THICKNESS, 1/4_THICKNESS, 1/2_THICKNESS, 3/4_THICKNESS, AREA, AOA, CHORD, 
%    MAX_THICKNESS_SEC1, MAX_THICKNESS_SEC2, MAX_THICKNESS_SEC3, MAX_THICKNESS_SEC4, MAX_THICKNESS_SEC5, 
%    1/4_THICKNESS_SEC1, 1/4_THICKNESS_SEC2, 1/4_THICKNESS_SEC3, 1/4_THICKNESS_SEC4, 1/4_THICKNESS_SEC5, 
%    1/2_THICKNESS_SEC1, 1/2_THICKNESS_SEC2, 1/2_THICKNESS_SEC3, 1/2_THICKNESS_SEC4, 1/2_THICKNESS_SEC5, 
%    3/4_THICKNESS_SEC1, 3/4_THICKNESS_SEC2, 3/4_THICKNESS_SEC3, 3/4_THICKNESS_SEC4, 3/4_THICKNESS_SEC5, 
%    AREA_SEC1, AREA_SEC2, AREA_SEC3, AREA_SEC4, AREA_SEC5, 
%    AOA_SEC1, AOA_SEC2, AOA_SEC3, AOA_SEC4, AOA_SEC5, 
%    CHORD_SEC1, CHORD_SEC2, CHORD_SEC3, CHORD_SEC4, CHORD_SEC5
%
% Available design variables
%    HICKS_HENNE 	(  1, Scale | Mark. List | Lower(0)/Upper(1) side, x_Loc )
%    COSINE_BUMP	(  2, Scale | Mark. List | Lower(0)/Upper(1) side, x_Loc, x_Size )
%    SPHERICAL		(  3, Scale | Mark. List | ControlPoint_Index, Theta_Disp, R_Disp )
%    NACA_4DIGITS	(  4, Scale | Mark. List | 1st digit, 2nd digit, 3rd and 4th digit )
%    DISPLACEMENT	(  5, Scale | Mark. List | x_Disp, y_Disp, z_Disp )
%    ROTATION		(  6, Scale | Mark. List | x_Axis, y_Axis, z_Axis, x_Turn, y_Turn, z_Turn )
%    FFD_CONTROL_POINT	(  7, Scale | Mark. List | FFD_Box_ID, i_Ind, j_Ind, k_Ind, x_Mov, y_Mov, z_Mov )
%    FFD_DIHEDRAL_ANGLE	(  8, Scale | Mark. List | FFD_Box_ID, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
%    FFD_TWIST_ANGLE 	(  9, Scale | Mark. List | FFD_Box_ID, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
%    FFD_ROTATION 	( 10, Scale | Mark. List | FFD_Box_ID, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
%    FFD_CAMBER 	( 11, Scale | Mark. List | FFD_Box_ID, i_Ind, j_Ind )
%    FFD_THICKNESS 	( 12, Scale | Mark. List | FFD_Box_ID, i_Ind, j_Ind )
%    FOURIER 		( 14, Scale | Mark. List | Lower(0)/Upper(1) side, index, cos(0)/sin(1) )
%    FFD_CONTROL_POINT_2D (  15, Scale | Mark. List | FFD_Box_ID, i_Ind, j_Ind, x_Mov, y_Mov )
%    FFD_CAMBER_2D 	( 16, Scale | Mark. List | FFD_Box_ID, i_Ind )
%    FFD_THICKNESS_2D 	( 17, Scale | Mark. List | FFD_Box_ID, i_Ind )
%
% Optimization objective function with scaling factor
% ex= Objective * Scale
OPT_OBJECTIVE= DRAG * 0.001
%
% Optimization constraint functions with scaling factors, separated by semicolons
% ex= (Objective = Value ) * Scale, use '>','<','='
OPT_CONSTRAINT= ( LIFT > 0.328188 ) * 0.001; ( MOMENT_Z > 0.034068 ) * 0.001; ( MAX_THICKNESS > 0.11 ) * 0.001
%
% Optimization design variables, separated by semicolons
DEFINITION_DV= ( 1, 1.0 | airfoil | 0, 0.05 ); ( 1, 1.0 | airfoil | 0, 0.10 ); ( 1, 1.0 | airfoil | 0, 0.15 ); ( 1, 1.0 | airfoil | 0, 0.20 ); ( 1, 1.0 | airfoil | 0, 0.25 ); ( 1, 1.0 | airfoil | 0, 0.30 ); ( 1, 1.0 | airfoil | 0, 0.35 ); ( 1, 1.0 | airfoil | 0, 0.40 ); ( 1, 1.0 | airfoil | 0, 0.45 ); ( 1, 1.0 | airfoil | 0, 0.50 ); ( 1, 1.0 | airfoil | 0, 0.55 ); ( 1, 1.0 | airfoil | 0, 0.60 ); ( 1, 1.0 | airfoil | 0, 0.65 ); ( 1, 1.0 | airfoil | 0, 0.70 ); ( 1, 1.0 | airfoil | 0, 0.75 ); ( 1, 1.0 | airfoil | 0, 0.80 ); ( 1, 1.0 | airfoil | 0, 0.85 ); ( 1, 1.0 | airfoil | 0, 0.90 ); ( 1, 1.0 | airfoil | 0, 0.95 ); ( 1, 1.0 | airfoil | 1, 0.05 ); ( 1, 1.0 | airfoil | 1, 0.10 ); ( 1, 1.0 | airfoil | 1, 0.15 ); ( 1, 1.0 | airfoil | 1, 0.20 ); ( 1, 1.0 | airfoil | 1, 0.25 ); ( 1, 1.0 | airfoil | 1, 0.30 ); ( 1, 1.0 | airfoil | 1, 0.35 ); ( 1, 1.0 | airfoil | 1, 0.40 ); ( 1, 1.0 | airfoil | 1, 0.45 ); ( 1, 1.0 | airfoil | 1, 0.50 ); ( 1, 1.0 | airfoil | 1, 0.55 ); ( 1, 1.0 | airfoil | 1, 0.60 ); ( 1, 1.0 | airfoil | 1, 0.65 ); ( 1, 1.0 | airfoil | 1, 0.70 ); ( 1, 1.0 | airfoil | 1, 0.75 ); ( 1, 1.0 | airfoil | 1, 0.80 ); ( 1, 1.0 | airfoil | 1, 0.85 ); ( 1, 1.0 | airfoil | 1, 0.90 ); ( 1, 1.0 | airfoil | 1, 0.95 )