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Merge pull request #32 from su2code/develop
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‎compressible_flow/Transitional_Airfoil/Langtry_and_Menter/E387/ogrid_e387.su2

+295,836
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‎compressible_flow/Transitional_Airfoil/Langtry_and_Menter/E387/transitional_SA_LM_model_ConfigFile.cfg

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: Eppler E387 Airfoil at Re = 200K %
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% Author: Andrea Rausa %
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% Institution: Politecnico di Milano %
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% Date: Dec 07th, 2022 %
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% File Version 7.5.0 "Blackbird" %
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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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SOLVER= RANS
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%
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KIND_TURB_MODEL= SA
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KIND_TRANS_MODEL= LM
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FREESTREAM_TURBULENCEINTENSITY= 0.001
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%
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MATH_PROBLEM= DIRECT
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%
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RESTART_SOL= NO
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%
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% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
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%
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MACH_NUMBER= 0.06
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%
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AOA= 2
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%
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FREESTREAM_TEMPERATURE= 288.15
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%
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REYNOLDS_NUMBER= 200000.0
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%
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REYNOLDS_LENGTH= 1.0
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% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
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%
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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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REF_LENGTH= 1.0
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%
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REF_AREA= 0
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%
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REF_DIMENSIONALIZATION= FREESTREAM_VEL_EQ_MACH
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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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%
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MARKER_HEATFLUX= ( Airfoil, 0.0 )
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%
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MARKER_FAR= ( Farfield )
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%
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MARKER_PLOTTING= ( Airfoil )
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%
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MARKER_MONITORING= ( Airfoil )
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% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
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%
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NUM_METHOD_GRAD= GREEN_GAUSS
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%
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CFL_NUMBER= 1
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%
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%MAX_DELTA_TIME= 1E10
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%
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CFL_ADAPT= YES
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%
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CFL_ADAPT_PARAM= ( 0.1, 2.0, 40.0, 1e10, 0.001 )
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%
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ITER= 100000
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% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
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%
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LINEAR_SOLVER= FGMRES
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%
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LINEAR_SOLVER_PREC= LU_SGS
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%
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LINEAR_SOLVER_ERROR= 1E-6
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%
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LINEAR_SOLVER_ITER= 5
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% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
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%
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CONV_NUM_METHOD_FLOW= ROE
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USE_VECTORIZATION= NO
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%
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MUSCL_FLOW= YES
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%
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SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
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%
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JST_SENSOR_COEFF= ( 0.5, 0.02 )
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%
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TIME_DISCRE_FLOW= EULER_IMPLICIT
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% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
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%
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VENKAT_LIMITER_COEFF= 0.05
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%
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LIMITER_ITER= 99999
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% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
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%
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CONV_NUM_METHOD_TURB= SCALAR_UPWIND
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%
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MUSCL_TURB= NO
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%
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SLOPE_LIMITER_TURB= NONE
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%
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TIME_DISCRE_TURB= EULER_IMPLICIT
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%
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CFL_REDUCTION_TURB= 1.0
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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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%
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CONV_RESIDUAL_MINVAL= -13
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%
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CONV_FIELD= ( RMS_DENSITY )
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%
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CONV_STARTITER= 500
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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%
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MESH_FILENAME= ogrid_e387.su2
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%
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MESH_FORMAT= SU2
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%
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MESH_OUT_FILENAME= mesh_out.su2
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%
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SOLUTION_FILENAME= restart_flow.dat
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%
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OUTPUT_FILES= (RESTART, PARAVIEW, SURFACE_PARAVIEW)
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WRT_FORCES_BREAKDOWN= YES
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VOLUME_OUTPUT= (COORDINATES, SOLUTION, PRIMITIVE, RESIDUAL)
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HISTORY_OUTPUT= (ITER, LINSOL, RMS_RES, MAX_RES, AERO_COEFF, CFL_NUMBER)
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%
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CONV_FILENAME= historySecond
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%
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RESTART_FILENAME= restart_flow.dat
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%
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VOLUME_FILENAME= flow
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%
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SURFACE_FILENAME= surface_flow
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%
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OUTPUT_WRT_FREQ= 500
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%
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SCREEN_WRT_FREQ_INNER= 10
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%
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SCREEN_OUTPUT=(INNER_ITER, WALL_TIME, RMS_DENSITY, RMS_INTERMITTENCY, RMS_RE_THETA_T, LIFT, DRAG, LINSOL_ITER_TRANS, LINSOL_RESIDUAL_TRANS)
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%
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WRT_PERFORMANCE = YES

‎compressible_flow/Transitional_Airfoil/Langtry_and_Menter/E387/transitional_SST_LM_model_ConfigFile.cfg

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: Eppler E387 Airfoil at Re = 200K %
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% Author: Andrea Rausa %
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% Institution: Politecnico di Milano %
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% Date: Dec 07th, 2022 %
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% File Version 7.5.0 "Blackbird" %
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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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SOLVER= RANS
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%
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KIND_TURB_MODEL= SST
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KIND_TRANS_MODEL= LM
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FREESTREAM_TURBULENCEINTENSITY= 0.001
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%
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MATH_PROBLEM= DIRECT
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%
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RESTART_SOL= NO
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%
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% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
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%
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MACH_NUMBER= 0.06
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%
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AOA= 2
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%
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FREESTREAM_TEMPERATURE= 288.15
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%
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REYNOLDS_NUMBER= 200000.0
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%
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REYNOLDS_LENGTH= 1.0
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% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
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%
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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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REF_LENGTH= 1.0
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%
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REF_AREA= 0
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%
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REF_DIMENSIONALIZATION= FREESTREAM_VEL_EQ_MACH
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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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%
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MARKER_HEATFLUX= ( Airfoil, 0.0 )
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%
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MARKER_FAR= ( Farfield )
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%
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MARKER_PLOTTING= ( Airfoil )
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%
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MARKER_MONITORING= ( Airfoil )
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% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
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%
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NUM_METHOD_GRAD= GREEN_GAUSS
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%
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CFL_NUMBER= 1
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%
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%MAX_DELTA_TIME= 1E10
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%
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CFL_ADAPT= YES
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%
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CFL_ADAPT_PARAM= ( 0.1, 2.0, 40.0, 1e10, 0.001 )
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%
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ITER= 100000
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% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
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%
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LINEAR_SOLVER= FGMRES
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%
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LINEAR_SOLVER_PREC= LU_SGS
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%
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LINEAR_SOLVER_ERROR= 1E-6
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%
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LINEAR_SOLVER_ITER= 5
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% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
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%
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CONV_NUM_METHOD_FLOW= ROE
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USE_VECTORIZATION= NO
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%
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MUSCL_FLOW= YES
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%
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SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
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%
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JST_SENSOR_COEFF= ( 0.5, 0.02 )
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%
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TIME_DISCRE_FLOW= EULER_IMPLICIT
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% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
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%
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VENKAT_LIMITER_COEFF= 0.05
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%
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LIMITER_ITER= 99999
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% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
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%
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CONV_NUM_METHOD_TURB= SCALAR_UPWIND
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%
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MUSCL_TURB= YES
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%
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SLOPE_LIMITER_TURB= NONE
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%
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TIME_DISCRE_TURB= EULER_IMPLICIT
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%
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CFL_REDUCTION_TURB= 1.0
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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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%
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CONV_RESIDUAL_MINVAL= -13
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%
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CONV_FIELD= ( RMS_DENSITY )
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%
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CONV_STARTITER= 500
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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%
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MESH_FILENAME= ogrid_e387.su2
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%
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MESH_FORMAT= SU2
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%
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SOLUTION_FILENAME= restart_flow.dat
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%
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OUTPUT_FILES= (RESTART)
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WRT_FORCES_BREAKDOWN= YES
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VOLUME_OUTPUT= (COORDINATES, SOLUTION, PRIMITIVE, RESIDUAL)
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HISTORY_OUTPUT= (ITER, LINSOL, RMS_RES, MAX_RES, AERO_COEFF, CFL_NUMBER)
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%
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CONV_FILENAME= historySecond
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%
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RESTART_FILENAME= restart_flow.dat
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%
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VOLUME_FILENAME= flow
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%
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SURFACE_FILENAME= surface_flow
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%
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OUTPUT_WRT_FREQ= 500
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%
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SCREEN_WRT_FREQ_INNER= 10
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%
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SCREEN_OUTPUT=(INNER_ITER, WALL_TIME, RMS_DENSITY, RMS_INTERMITTENCY, RMS_RE_THETA_T, LIFT, DRAG, LINSOL_ITER_TRANS, LINSOL_RESIDUAL_TRANS)
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%
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WRT_PERFORMANCE = YES

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