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Added rough flatplate test cases
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‎TestCases/rans/flatplate/roughness/bc_aupoix/turb_SST_flatplate_roughBCAupoix.cfg‎

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: Turbulent flow over flat plate with zero pressure gradient %
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% Author: Thomas D. Economon %
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% Institution: Stanford University %
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% Date: 2011.11.10 %
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% File Version 5.0.0 "Raven" %
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% %
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
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%
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% Physical governing equations (EULER, NAVIER_STOKES,
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% WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY,
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% POISSON_EQUATION)
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SOLVER= RANS
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%
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% If Navier-Stokes, kind of turbulent model (NONE, SA, SA_NEG, SST)
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KIND_TURB_MODEL= SST
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WALL_ROUGHNESS = (wall, 400e-6)
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KIND_ROUGHSST_MODEL = LIMITER_AUPOIX
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%
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% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
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MATH_PROBLEM= DIRECT
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%
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% Restart solution (NO, YES)
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RESTART_SOL= NO
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READ_BINARY_RESTART= YES
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% ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------%
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%
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% Mach number (non-dimensional, based on the free-stream values)
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MACH_NUMBER= 0.2
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%
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% Angle of attack (degrees)
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AOA= 0.0
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%
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% Side-slip angle (degrees)
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SIDESLIP_ANGLE= 0.0
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%
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% Free-stream temperature (288.15 K by default)
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FREESTREAM_TEMPERATURE= 300.0
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%
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% Reynolds number (non-dimensional, based on the free-stream values)
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REYNOLDS_NUMBER= 5000000.0
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%
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% Reynolds length (in meters)
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REYNOLDS_LENGTH= 1.0
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% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
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%
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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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%
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% Reference length for pitching, rolling, and yawing non-dimensional moment
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REF_LENGTH= 1.0
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%
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% Reference area for force coefficients (0 implies automatic calculation)
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REF_AREA= 2.0
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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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%
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% Navier-Stokes wall boundary marker(s) (NONE = no marker)
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MARKER_HEATFLUX= ( wall, 0.0 )
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%
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% Inlet boundary marker(s) (NONE = no marker)
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% Format: ( inlet marker, total temperature, total pressure, flow_direction_x,
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% flow_direction_y, flow_direction_z, ... )
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MARKER_INLET= ( inlet, 302.4, 118309.784, 1.0, 0.0, 0.0 )
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%
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% Outlet boundary marker(s) (NONE = no marker)
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% Format: ( outlet marker, back pressure, ... )
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MARKER_OUTLET= ( outlet, 115056.0, farfield, 115056.0 )
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%
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% Symmetry boundary marker(s) (NONE = no marker)
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MARKER_SYM= ( symmetry )
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%
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% Marker(s) of the surface to be plotted or designed
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MARKER_PLOTTING= ( wall )
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%
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% Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated
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MARKER_MONITORING= ( wall )
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% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
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%
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% Numerical method for spatial gradients (GREEN_GAUSS, LEAST_SQUARES,
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% WEIGHTED_LEAST_SQUARES)
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NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
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%
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% Courant-Friedrichs-Lewy condition of the finest grid
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CFL_NUMBER= 100.0
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%
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% Adaptive CFL number (NO, YES)
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CFL_ADAPT= YES
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%
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% Parameters of the adaptive CFL number (factor down, factor up, CFL min value,
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% CFL max value )
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CFL_ADAPT_PARAM= ( 0.1, 2.0, 100.0, 1e5 )
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%
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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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%
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% Number of total iterations
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ITER= 99999
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% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
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%
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% Coefficient for the limiter
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VENKAT_LIMITER_COEFF= 0.1
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%
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% Coefficient for the sharp edges limiter
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ADJ_SHARP_LIMITER_COEFF= 3.0
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%
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% Reference coefficient (sensitivity) for detecting sharp edges.
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REF_SHARP_EDGES= 3.0
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%
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% Remove sharp edges from the sensitivity evaluation (NO, YES)
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SENS_REMOVE_SHARP= NO
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% -------------------------- MULTIGRID PARAMETERS -----------------------------%
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%
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% Multi-Grid Levels (0 = no multi-grid)
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MGLEVEL= 0
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%
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% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE)
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MGCYCLE= V_CYCLE
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%
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% Multi-grid pre-smoothing level
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MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
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%
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% Multi-grid post-smoothing level
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MG_POST_SMOOTH= ( 2, 2, 2, 2)
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%
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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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%
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% Damping factor for the residual restriction
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MG_DAMP_RESTRICTION= 0.8
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%
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% Damping factor for the correction prolongation
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MG_DAMP_PROLONGATION= 0.8
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% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
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%
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% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
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% TURKEL_PREC, MSW)
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CONV_NUM_METHOD_FLOW= ROE
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%
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% Monotonic Upwind Scheme for Conservation Laws (TVD) in the flow equations.
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% Required for 2nd order upwind schemes (NO, YES)
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MUSCL_FLOW= YES
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%
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% Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG,
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% BARTH_JESPERSEN, VAN_ALBADA_EDGE)
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SLOPE_LIMITER_FLOW= NONE
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%
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% 2nd and 4th order artificial dissipation coefficients
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JST_SENSOR_COEFF= ( 0.5, 0.02 )
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%
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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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% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
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%
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% Convective numerical method (SCALAR_UPWIND)
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CONV_NUM_METHOD_TURB= SCALAR_UPWIND
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%
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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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MUSCL_TURB= NO
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%
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% Slope limiter (VENKATAKRISHNAN, MINMOD)
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SLOPE_LIMITER_TURB= VENKATAKRISHNAN
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%
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% Time discretization (EULER_IMPLICIT)
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TIME_DISCRE_TURB= EULER_IMPLICIT
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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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%
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% Convergence criteria (CAUCHY, RESIDUAL)
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CONV_FIELD= RMS_DENSITY
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%
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% Min value of the residual (log10 of the residual)
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CONV_RESIDUAL_MINVAL= -14
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%
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% Start convergence criteria at iteration number
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CONV_STARTITER= 10
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%
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% Number of elements to apply the criteria
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CONV_CAUCHY_ELEMS= 100
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%
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% Epsilon to control the series convergence
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CONV_CAUCHY_EPS= 1E-6
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%
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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%
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% Mesh input file
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MESH_FILENAME= mesh_flatplate_turb_137x97.su2
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%
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% Mesh input file format (SU2, CGNS, NETCDF_ASCII)
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MESH_FORMAT= SU2
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%
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% Mesh output file
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MESH_OUT_FILENAME= mesh_out.su2
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%
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% Restart flow input file
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SOLUTION_FILENAME= solution_flow.dat
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%
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% Restart adjoint input file
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SOLUTION_ADJ_FILENAME= solution_adj.dat
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%
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% Output file format (PARAVIEW, TECPLOT, SLT)
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TABULAR_FORMAT= CSV
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%
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% Output file convergence history (w/o extension)
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CONV_FILENAME= history
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%
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% Output file restart flow
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RESTART_FILENAME= restart_flow.dat
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%
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% Output file restart adjoint
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RESTART_ADJ_FILENAME= restart_adj.dat
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%
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% Output file flow (w/o extension) variables
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VOLUME_FILENAME= flow
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%
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% Output file adjoint (w/o extension) variables
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VOLUME_ADJ_FILENAME= adjoint
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%
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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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%
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% Output file surface flow coefficient (w/o extension)
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SURFACE_FILENAME= surface_flow
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%
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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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%
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% Writing solution file frequency
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OUTPUT_WRT_FREQ= 1000
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%
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%
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% Screen output
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SCREEN_OUTPUT= (INNER_ITER, WALL_TIME, RMS_RES, LIFT, DRAG)

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