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compressible_flow/Transitional_Airfoil/Langtry_and_Menter/E387/ogrid_e387.su2
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151 changes: 151 additions & 0 deletions
151
...flow/Transitional_Airfoil/Langtry_and_Menter/E387/transitional_SA_LM_model_ConfigFile.cfg
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% | ||
% % | ||
% SU2 configuration file % | ||
% Case description: Eppler E387 Airfoil at Re = 200K % | ||
% Author: Andrea Rausa % | ||
% Institution: Politecnico di Milano % | ||
% Date: Dec 07th, 2022 % | ||
% File Version 7.5.0 "Blackbird" % | ||
% % | ||
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% | ||
|
||
% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% | ||
% | ||
SOLVER= RANS | ||
% | ||
KIND_TURB_MODEL= SA | ||
KIND_TRANS_MODEL= LM | ||
FREESTREAM_TURBULENCEINTENSITY= 0.001 | ||
% | ||
MATH_PROBLEM= DIRECT | ||
% | ||
RESTART_SOL= NO | ||
% | ||
|
||
% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------% | ||
% | ||
MACH_NUMBER= 0.06 | ||
% | ||
AOA= 2 | ||
% | ||
FREESTREAM_TEMPERATURE= 288.15 | ||
% | ||
REYNOLDS_NUMBER= 200000.0 | ||
% | ||
REYNOLDS_LENGTH= 1.0 | ||
|
||
% ---------------------- REFERENCE VALUE DEFINITION ---------------------------% | ||
% | ||
REF_ORIGIN_MOMENT_X= 0.25 | ||
REF_ORIGIN_MOMENT_Y = 0.00 | ||
REF_ORIGIN_MOMENT_Z = 0.00 | ||
% | ||
REF_LENGTH= 1.0 | ||
% | ||
REF_AREA= 0 | ||
% | ||
REF_DIMENSIONALIZATION= FREESTREAM_VEL_EQ_MACH | ||
|
||
% -------------------- BOUNDARY CONDITION DEFINITION --------------------------% | ||
% | ||
MARKER_HEATFLUX= ( Airfoil, 0.0 ) | ||
% | ||
MARKER_FAR= ( Farfield ) | ||
% | ||
MARKER_PLOTTING= ( Airfoil ) | ||
% | ||
MARKER_MONITORING= ( Airfoil ) | ||
|
||
% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------% | ||
% | ||
NUM_METHOD_GRAD= GREEN_GAUSS | ||
% | ||
CFL_NUMBER= 1 | ||
% | ||
%MAX_DELTA_TIME= 1E10 | ||
% | ||
CFL_ADAPT= YES | ||
% | ||
CFL_ADAPT_PARAM= ( 0.1, 2.0, 40.0, 1e10, 0.001 ) | ||
% | ||
ITER= 100000 | ||
|
||
% ------------------------ LINEAR SOLVER DEFINITION ---------------------------% | ||
% | ||
LINEAR_SOLVER= FGMRES | ||
% | ||
LINEAR_SOLVER_PREC= LU_SGS | ||
% | ||
LINEAR_SOLVER_ERROR= 1E-6 | ||
% | ||
LINEAR_SOLVER_ITER= 5 | ||
|
||
% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------% | ||
% | ||
CONV_NUM_METHOD_FLOW= ROE | ||
USE_VECTORIZATION= NO | ||
% | ||
MUSCL_FLOW= YES | ||
% | ||
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN | ||
% | ||
JST_SENSOR_COEFF= ( 0.5, 0.02 ) | ||
% | ||
TIME_DISCRE_FLOW= EULER_IMPLICIT | ||
|
||
% ----------------------- SLOPE LIMITER DEFINITION ----------------------------% | ||
% | ||
VENKAT_LIMITER_COEFF= 0.05 | ||
% | ||
LIMITER_ITER= 99999 | ||
|
||
% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------% | ||
% | ||
CONV_NUM_METHOD_TURB= SCALAR_UPWIND | ||
% | ||
MUSCL_TURB= NO | ||
% | ||
SLOPE_LIMITER_TURB= NONE | ||
% | ||
TIME_DISCRE_TURB= EULER_IMPLICIT | ||
% | ||
CFL_REDUCTION_TURB= 1.0 | ||
|
||
% --------------------------- CONVERGENCE PARAMETERS --------------------------% | ||
% | ||
CONV_RESIDUAL_MINVAL= -13 | ||
% | ||
CONV_FIELD= ( RMS_DENSITY ) | ||
% | ||
CONV_STARTITER= 500 | ||
|
||
% ------------------------- INPUT/OUTPUT INFORMATION --------------------------% | ||
% | ||
MESH_FILENAME= ogrid_e387.su2 | ||
% | ||
MESH_FORMAT= SU2 | ||
% | ||
MESH_OUT_FILENAME= mesh_out.su2 | ||
% | ||
SOLUTION_FILENAME= restart_flow.dat | ||
% | ||
OUTPUT_FILES= (RESTART, PARAVIEW, SURFACE_PARAVIEW) | ||
WRT_FORCES_BREAKDOWN= YES | ||
VOLUME_OUTPUT= (COORDINATES, SOLUTION, PRIMITIVE, RESIDUAL) | ||
HISTORY_OUTPUT= (ITER, LINSOL, RMS_RES, MAX_RES, AERO_COEFF, CFL_NUMBER) | ||
% | ||
CONV_FILENAME= historySecond | ||
% | ||
RESTART_FILENAME= restart_flow.dat | ||
% | ||
VOLUME_FILENAME= flow | ||
% | ||
SURFACE_FILENAME= surface_flow | ||
% | ||
OUTPUT_WRT_FREQ= 500 | ||
% | ||
SCREEN_WRT_FREQ_INNER= 10 | ||
% | ||
SCREEN_OUTPUT=(INNER_ITER, WALL_TIME, RMS_DENSITY, RMS_INTERMITTENCY, RMS_RE_THETA_T, LIFT, DRAG, LINSOL_ITER_TRANS, LINSOL_RESIDUAL_TRANS) | ||
% | ||
WRT_PERFORMANCE = YES |
150 changes: 150 additions & 0 deletions
150
...low/Transitional_Airfoil/Langtry_and_Menter/E387/transitional_SST_LM_model_ConfigFile.cfg
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@@ -0,0 +1,150 @@ | ||
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% | ||
% % | ||
% SU2 configuration file % | ||
% Case description: Eppler E387 Airfoil at Re = 200K % | ||
% Author: Andrea Rausa % | ||
% Institution: Politecnico di Milano % | ||
% Date: Dec 07th, 2022 % | ||
% File Version 7.5.0 "Blackbird" % | ||
% % | ||
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% | ||
|
||
% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% | ||
% | ||
SOLVER= RANS | ||
% | ||
KIND_TURB_MODEL= SST | ||
KIND_TRANS_MODEL= LM | ||
FREESTREAM_TURBULENCEINTENSITY= 0.001 | ||
% | ||
MATH_PROBLEM= DIRECT | ||
% | ||
RESTART_SOL= NO | ||
% | ||
|
||
% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------% | ||
% | ||
MACH_NUMBER= 0.06 | ||
% | ||
AOA= 2 | ||
% | ||
FREESTREAM_TEMPERATURE= 288.15 | ||
% | ||
REYNOLDS_NUMBER= 200000.0 | ||
% | ||
REYNOLDS_LENGTH= 1.0 | ||
|
||
% ---------------------- REFERENCE VALUE DEFINITION ---------------------------% | ||
% | ||
REF_ORIGIN_MOMENT_X= 0.25 | ||
REF_ORIGIN_MOMENT_Y = 0.00 | ||
REF_ORIGIN_MOMENT_Z = 0.00 | ||
% | ||
REF_LENGTH= 1.0 | ||
% | ||
REF_AREA= 0 | ||
% | ||
REF_DIMENSIONALIZATION= FREESTREAM_VEL_EQ_MACH | ||
|
||
% -------------------- BOUNDARY CONDITION DEFINITION --------------------------% | ||
% | ||
MARKER_HEATFLUX= ( Airfoil, 0.0 ) | ||
% | ||
MARKER_FAR= ( Farfield ) | ||
% | ||
MARKER_PLOTTING= ( Airfoil ) | ||
% | ||
MARKER_MONITORING= ( Airfoil ) | ||
|
||
% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------% | ||
% | ||
NUM_METHOD_GRAD= GREEN_GAUSS | ||
% | ||
CFL_NUMBER= 1 | ||
% | ||
%MAX_DELTA_TIME= 1E10 | ||
% | ||
CFL_ADAPT= YES | ||
% | ||
CFL_ADAPT_PARAM= ( 0.1, 2.0, 40.0, 1e10, 0.001 ) | ||
% | ||
ITER= 100000 | ||
|
||
% ------------------------ LINEAR SOLVER DEFINITION ---------------------------% | ||
% | ||
LINEAR_SOLVER= FGMRES | ||
% | ||
LINEAR_SOLVER_PREC= LU_SGS | ||
% | ||
LINEAR_SOLVER_ERROR= 1E-6 | ||
% | ||
LINEAR_SOLVER_ITER= 5 | ||
|
||
% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------% | ||
% | ||
CONV_NUM_METHOD_FLOW= ROE | ||
USE_VECTORIZATION= NO | ||
% | ||
MUSCL_FLOW= YES | ||
% | ||
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN | ||
% | ||
JST_SENSOR_COEFF= ( 0.5, 0.02 ) | ||
% | ||
TIME_DISCRE_FLOW= EULER_IMPLICIT | ||
|
||
% ----------------------- SLOPE LIMITER DEFINITION ----------------------------% | ||
% | ||
VENKAT_LIMITER_COEFF= 0.05 | ||
% | ||
LIMITER_ITER= 99999 | ||
|
||
% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------% | ||
% | ||
CONV_NUM_METHOD_TURB= SCALAR_UPWIND | ||
% | ||
MUSCL_TURB= YES | ||
% | ||
SLOPE_LIMITER_TURB= NONE | ||
% | ||
TIME_DISCRE_TURB= EULER_IMPLICIT | ||
% | ||
CFL_REDUCTION_TURB= 1.0 | ||
|
||
% --------------------------- CONVERGENCE PARAMETERS --------------------------% | ||
% | ||
CONV_RESIDUAL_MINVAL= -13 | ||
% | ||
CONV_FIELD= ( RMS_DENSITY ) | ||
% | ||
CONV_STARTITER= 500 | ||
|
||
|
||
% ------------------------- INPUT/OUTPUT INFORMATION --------------------------% | ||
% | ||
MESH_FILENAME= ogrid_e387.su2 | ||
% | ||
MESH_FORMAT= SU2 | ||
% | ||
SOLUTION_FILENAME= restart_flow.dat | ||
% | ||
OUTPUT_FILES= (RESTART) | ||
WRT_FORCES_BREAKDOWN= YES | ||
VOLUME_OUTPUT= (COORDINATES, SOLUTION, PRIMITIVE, RESIDUAL) | ||
HISTORY_OUTPUT= (ITER, LINSOL, RMS_RES, MAX_RES, AERO_COEFF, CFL_NUMBER) | ||
% | ||
CONV_FILENAME= historySecond | ||
% | ||
RESTART_FILENAME= restart_flow.dat | ||
% | ||
VOLUME_FILENAME= flow | ||
% | ||
SURFACE_FILENAME= surface_flow | ||
% | ||
OUTPUT_WRT_FREQ= 500 | ||
% | ||
SCREEN_WRT_FREQ_INNER= 10 | ||
% | ||
SCREEN_OUTPUT=(INNER_ITER, WALL_TIME, RMS_DENSITY, RMS_INTERMITTENCY, RMS_RE_THETA_T, LIFT, DRAG, LINSOL_ITER_TRANS, LINSOL_RESIDUAL_TRANS) | ||
% | ||
WRT_PERFORMANCE = YES |
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