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Merged
pcarruscag merged 5 commits into from
Dec 20, 2022
Merged

Update master #32

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5e59ebe
changing PASSIVE_SCALAR to SPECIES_TRANSPORT
Oct 5, 2022
5005cb7
Merge pull request #27 from su2code/feature_species_transport
Cristopher-Morales Oct 5, 2022
c72907f
Tutorials LM model for T3A, T3A-, and NLF-0416 airfoil (#28)
sun5k Oct 25, 2022
7c92a14
Update Config files. (#30)
sun5k Oct 30, 2022
56e22f6
Additional files for LM transition model (#31)
rois1995 Dec 18, 2022
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295,836 changes: 295,836 additions & 0 deletions compressible_flow/Transitional_Airfoil/Langtry_and_Menter/E387/ogrid_e387.su2
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151 changes: 151 additions & 0 deletions ...flow/Transitional_Airfoil/Langtry_and_Menter/E387/transitional_SA_LM_model_ConfigFile.cfg
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Original file line number Diff line number Diff line change
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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 ...low/Transitional_Airfoil/Langtry_and_Menter/E387/transitional_SST_LM_model_ConfigFile.cfg
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Original file line number Diff line number Diff line change
@@ -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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