Tutorials/compressible_flow/NICFD_nozzle/PhysicsInformed/config_NICFD_PINN.cfg at 8205ce14e570d18e965f5174e57716c5cbc34789 · su2code/Tutorials · GitHub

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%                                                                              %
% SU2 configuration file, automatically generated with "3_run_SU2.py"          %
% Case description: Non-ideal compressible fluid flow in a converging-         %
%                   diverging supersonic nozzle using a PINN for thermodynamic %
%                   state calculations.                                        %
% Author: Evert Bunschoten                                                     %
% Institution: Delft University of Technology                                  %
% Date: 2025.3.26                                                              %
% File Version  8.1.0 "Harrier"                                                %
%                                                                              %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%


SOLVER= RANS
KIND_TURB_MODEL= SA
SA_OPTIONS= NONE
RESTART_SOL=NO
MACH_NUMBER= 0.05
AoA= 0.0

FREESTREAM_PRESSURE= 1.809444e+06

FREESTREAM_TEMPERATURE= 5.229862e+02

FREESTREAM_TURBULENCEINTENSITY = 0.1

FREESTREAM_TURB2LAMVISCRATIO = 100.0

FREESTREAM_OPTION= TEMPERATURE_FS

INIT_OPTION= TD_CONDITIONS

REF_DIMENSIONALIZATION= DIMENSIONAL

FLUID_MODEL= DATADRIVEN_FLUID
USE_PINN=YES
INTERPOLATION_METHOD = MLP
FILENAMES_INTERPOLATOR = (MLP_siloxane_MM.mlp)

VISCOSITY_MODEL= CONSTANT_VISCOSITY

MU_CONSTANT= 1.0e-05

CONDUCTIVITY_MODEL= CONSTANT_PRANDTL
PRANDTL_LAM=8.25e-01
TURBULENT_CONDUCTIVITY_MODEL=CONSTANT_PRANDTL_TURB
PRANDTL_TURB=8.25e-01

MARKER_HEATFLUX= (wall, 0.0)

MARKER_MONITORING=(wall)

MARKER_EULER=(symmetry)

MARKER_GILES= (inflow, TOTAL_CONDITIONS_PT, 1.809444e+06, 5.229862e+02, 1.0, 0.0, 0.0, 0.8, 0.8,\
               outflow, STATIC_PRESSURE,1.809444e+05, 0.0, 0.0, 0.0, 0.0, 0.8, 0.8)
SPATIAL_FOURIER=NO
TURBOMACHINERY_KIND= AXIAL
TURBO_PERF_KIND=TURBINE
RAMP_OUTLET=NO
RAMP_OUTLET_COEFF= (1.809444e+06, 10, 200)
AVERAGE_PROCESS_KIND= AREA
MIXEDOUT_COEFF=(0.1, 1e-5, 15.0)
MARKER_TURBOMACHINERY= (inflow, outflow)

NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
CFL_NUMBER= 4
CFL_ADAPT= YES
CFL_ADAPT_PARAM= ( 0.99, 1.01, 1.0, 1000.0)

LINEAR_SOLVER= FGMRES
LINEAR_SOLVER_PREC= LU_SGS
LINEAR_SOLVER_ERROR= 1E-5
LINEAR_SOLVER_ITER= 10


CONV_NUM_METHOD_FLOW= ROE
MUSCL_FLOW= NO
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
VENKAT_LIMITER_COEFF=0.5

TIME_DISCRE_FLOW= EULER_IMPLICIT
CONV_NUM_METHOD_TURB= SCALAR_UPWIND
MUSCL_TURB = NO
SLOPE_LIMITER_TURB= VENKATAKRISHNAN
TIME_DISCRE_TURB= EULER_IMPLICIT
CFL_REDUCTION_TURB= 0.1

ITER=10000

CONV_RESIDUAL_MINVAL= -16
CONV_STARTITER= 10
CONV_CAUCHY_ELEMS= 100
CONV_CAUCHY_EPS= 1E-6
CONV_FILENAME=history_adjoint.csv
MESH_FILENAME= nozzle_mesh.su2

OUTPUT_WRT_FREQ= 20
OUTPUT_FILES=RESTART,PARAVIEW_MULTIBLOCK
SCREEN_OUTPUT= (INNER_ITER, RMS_RES)
HISTORY_OUTPUT= (INNER_ITER, WALL_TIME, RMS_RES, CFL_NUMBER)
VOLUME_OUTPUT= (SOLUTION, PRIMITIVE, RESIDUAL, MPI)