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% SU2 configuration file %
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% Case description: Turbulent flow past the ONERA M6 wing %
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% Author: Thomas D. Economon %
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% Institution: Stanford University %
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% File Version 6.1.0 "Falcon" %
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% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
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% Physical governing equations (EULER, NAVIER_STOKES,
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% WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY,
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PHYSICAL_PROBLEM= EULER
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% Specify turbulence model (NONE, SA, SA_NEG, SST)
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% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
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% Restart solution (NO, YES)
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% Number of mesh domains (Default 1)
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% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
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% Mach number (non-dimensional, based on the free-stream values)
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% Angle of attack (degrees, only for compressible flows)
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% Side-slip angle (degrees, only for compressible flows)
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% Free-stream temperature (288.15 K by default)
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FREESTREAM_TEMPERATURE= 288.15
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% Reynolds number (non-dimensional, based on the free-stream values)
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REYNOLDS_NUMBER= 11.72E6
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% Reynolds length (1 m by default)
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REYNOLDS_LENGTH= 0.64607
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% ---- IDEAL GAS, POLYTROPIC, VAN DER WAALS AND PENG ROBINSON CONSTANTS -------%
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% Different gas model (STANDARD_AIR, IDEAL_GAS, VW_GAS, PR_GAS)
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FLUID_MODEL= STANDARD_AIR
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% Ratio of specific heats (1.4 default and the value is hardcoded
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% for the model STANDARD_AIR)
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% Specific gas constant (287.058 J/kg*K default and this value is hardcoded
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% for the model STANDARD_AIR)
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% Critical Temperature (131.00 K by default)
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CRITICAL_TEMPERATURE= 131.00
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% Critical Pressure (3588550.0 N/m^2 by default)
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CRITICAL_PRESSURE= 3588550.0
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% Critical Density (263.0 Kg/m3 by default)
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CRITICAL_DENSITY= 263.0
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% Acentric factor (0.035 (air))
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ACENTRIC_FACTOR= 0.035
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% --------------------------- VISCOSITY MODEL ---------------------------------%
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% Viscosity model (SUTHERLAND, CONSTANT_VISCOSITY).
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VISCOSITY_MODEL= SUTHERLAND
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% Molecular Viscosity that would be constant (1.716E-5 by default)
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% Sutherland Viscosity Ref (1.716E-5 default value for AIR SI)
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% Sutherland Temperature Ref (273.15 K default value for AIR SI)
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% Sutherland constant (110.4 default value for AIR SI)
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SUTHERLAND_CONSTANT= 110.4
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% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
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% Reference origin for moment computation
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REF_ORIGIN_MOMENT_X = 0.25
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REF_ORIGIN_MOMENT_Y = 0.00
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REF_ORIGIN_MOMENT_Z = 0.00
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% Reference length for pitching, rolling, and yawing non-dimensional moment
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% Reference area for force coefficients (0 implies automatic calculation)
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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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% Navier-Stokes wall boundary marker(s) (NONE = no marker)
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MARKER_EULER= ( airfoil )
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%MARKER_HEATFLUX= ( wall, 0.0 )
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%MARKER_ISOTHERMAL = ( wall )
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% Far-field boundary marker(s) (NONE = no marker)
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MARKER_FAR= ( farfield1, farfield2 )
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% Symmetry boundary marker(s) (NONE = no marker)
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MARKER_SYM= ( symm1, symm2)
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MARKER_INTERFACE= ( int1, int2)
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% Marker(s) of the surface to be plotted or designed
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MARKER_PLOTTING= ( airfoil )
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% Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated
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MARKER_MONITORING= ( airfoil )
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% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
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% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
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NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
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% Courant-Friedrichs-Lewy condition of the finest grid
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CFL_REDUCTION_TURB = 1.0
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% Adaptive CFL number (NO, YES)
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% Parameters of the adaptive CFL number (factor down, factor up, CFL min value,
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CFL_ADAPT_PARAM= ( 1.5, 0.5, 2.0, 6.0 )
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% Runge-Kutta alpha coefficients
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RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
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% Number of total iterations
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% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
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% Freeze the value of the limiter after a number of iterations
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% Linear solver for the implicit formulation (BCGSTAB, FGMRES)
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LINEAR_SOLVER= FGMRES
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% Preconditioner of the Krylov linear solver (ILU0, LU_SGS, LINELET, JACOBI)
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LINEAR_SOLVER_PREC= LU_SGS
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% Minimum error of the linear solver for implicit formulations
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LINEAR_SOLVER_ERROR= 1E-10
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% Max number of iterations of the linear solver for the implicit formulation
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LINEAR_SOLVER_ITER= 2
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% -------------------------- MULTIGRID PARAMETERS -----------------------------%
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% Multi-Grid Levels (0 = no multi-grid)
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% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE)
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% Multi-grid pre-smoothing level
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MG_PRE_SMOOTH= ( 1, 2, 2, 2 )
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% Multi-grid post-smoothing level
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MG_POST_SMOOTH= ( 2, 2, 2, 2 )
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% Jacobi implicit smoothing of the correction
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MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )
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% Damping factor for the residual restriction
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MG_DAMP_RESTRICTION= 0.7
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% Damping factor for the correction prolongation
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MG_DAMP_PROLONGATION= 0.7
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% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
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% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
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CONV_NUM_METHOD_FLOW= AUSM
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% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
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% Slope limiter (VENKATAKRISHNAN, MINMOD)
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SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
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% Coefficient for the limiter (smooth regions)
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VENKAT_LIMITER_COEFF= 5.0
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% Entropy fix coefficient (0.0 implies no entropy fixing, 1.0 implies scalar
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% artificial dissipation)
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ENTROPY_FIX_COEFF= 1.0
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% 1st, 2nd and 4th order artificial dissipation coefficients
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AD_COEFF_FLOW= ( 0.15, 0.5, 0.02 )
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% Viscous limiter (NO, YES)
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VISCOUS_LIMITER_FLOW= NO
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% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
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TIME_DISCRE_FLOW= EULER_IMPLICIT
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% Relaxation coefficient
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RELAXATION_FACTOR_FLOW= 1.0
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% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
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% Convective numerical method (SCALAR_UPWIND)
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CONV_NUM_METHOD_TURB= SCALAR_UPWIND
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% Monotonic Upwind Scheme for Conservation Laws (TVD) in the turbulence equations.
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% Required for 2nd order upwind schemes (NO, YES)
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% Slope limiter (VENKATAKRISHNAN, MINMOD)
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SLOPE_LIMITER_TURB= VENKATAKRISHNAN
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% Time discretization (EULER_IMPLICIT)
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TIME_DISCRE_TURB= EULER_IMPLICIT
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% Relaxation coefficient
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RELAXATION_FACTOR_TURB= 1.0
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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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% Convergence criteria (CAUCHY, RESIDUAL)
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CONV_CRITERIA= RESIDUAL
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% Residual reduction (order of magnitude with respect to the initial value)
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RESIDUAL_REDUCTION= 5
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% Min value of the residual (log10 of the residual)
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% Start convergence criteria at iteration number
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% Number of elements to apply the criteria
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% Epsilon to control the series convergence
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% Function to apply the criteria (LIFT, DRAG, NEARFIELD_PRESS, SENS_GEOMETRY,
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% SENS_MACH, DELTA_LIFT, DELTA_DRAG)
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CAUCHY_FUNC_FLOW= DRAG
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CAUCHY_FUNC_ADJFLOW= SENS_GEOMETRY
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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MESH_FILENAME1= points
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MESH_FILENAME2= faces
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MESH_FILENAME3= owner
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MESH_FILENAME4= neighbour
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MESH_FILENAME5= boundary
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% Mesh input file format (SU2, CGNS, NETCDF_ASCII)
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MESH_FORMAT= OPENFOAM
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MESH_OUT_FILENAME= mesh_out.su2
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% Restart flow input file
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SOLUTION_FLOW_FILENAME= solution_flow.dat
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% Restart adjoint input file
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SOLUTION_ADJ_FILENAME= solution_adj.dat
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% Output file format (PARAVIEW, TECPLOT, STL)
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OUTPUT_FORMAT= TECPLOT
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% Output file convergence history (w/o extension)
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CONV_FILENAME= history
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% Output file restart flow
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RESTART_FLOW_FILENAME= restart_flow.dat
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% Output file restart adjoint
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RESTART_ADJ_FILENAME= restart_adj.dat
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% Output file flow (w/o extension) variables
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VOLUME_FLOW_FILENAME= flow
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% Output file adjoint (w/o extension) variables
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VOLUME_ADJ_FILENAME= adjoint
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% Output objective function gradient (using continuous adjoint)
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GRAD_OBJFUNC_FILENAME= of_grad.dat
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% Output file surface flow coefficient (w/o extension)
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SURFACE_FLOW_FILENAME= surface_flow
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% Output file surface adjoint coefficient (w/o extension)
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SURFACE_ADJ_FILENAME= surface_adjoint
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% Writing solution file frequency
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WRT_SOL_FREQ= 250 %250
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% Writing convergence history frequency
added
removed
Testcases/Multizone/NACA0012/non Matching Line/inv_NACA0012.cfg
