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% %

% SU2 configuration file %

% Case description: Turbulent premixed high pressure combustion chamber. %

% Author: N. Beishuizen %

% Institution: Bosch Thermotechniek B.V. %

% Date: 2025/01/01 %

% File Version 8.0 "Harrier" %

% %

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% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%

%

SOLVER= INC_RANS

KIND_TURB_MODEL= SST

SST_OPTIONS= V1994m

RESTART_SOL= YES

MGLEVEL= 0

%

% temperature and density

FREESTREAM_TEMPERATURE = 673

FREESTREAM_DENSITY = 2.55

% ---------------- INCOMPRESSIBLE FLOW CONDITION DEFINITION -------------------%

%

INC_DENSITY_MODEL= VARIABLE

INC_DENSITY_INIT= 2.55

%

INC_VELOCITY_INIT= (40.00, 0.0, 0.0 )

%

INC_ENERGY_EQUATION= NO

INC_TEMPERATURE_INIT= 673.0

%

INC_NONDIM= DIMENSIONAL

%

% -------------------- FLUID PROPERTIES ------------------------------------- %

%

%FLUID_MODEL= CONSTANT_DENSITY

FLUID_MODEL= INC_IDEAL_GAS

%

CONDUCTIVITY_MODEL= CONSTANT_PRANDTL

%THERMAL_CONDUCTIVITY_CONSTANT= 0.0357

%

PRANDTL_LAM= 0.72

TURBULENT_CONDUCTIVITY_MODEL= CONSTANT_PRANDTL_TURB

%TURBULENT_CONDUCTIVITY_MODEL= NONE

PRANDTL_TURB= 0.90

%

%VISCOSITY_MODEL= SUTHERLAND

VISCOSITY_MODEL= POLYNOMIAL_VISCOSITY

% polynomial viscosity for methane-air (phi=0.50)

MU_POLYCOEFFS= (1.097e-5, 3.437e-8, 3.332e-12, 0, 0)

MU_CONSTANT= 1.716E-5

MU_REF = 1.716e-5

MU_T_REF= 273.15

SUTHERLAND_CONSTANT = 110.4

SPECIFIC_HEAT_CP = 1350

%

% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%

%

MARKER_HEATFLUX= ( wall_top, 0.0, wall_side, 0.0, wall_pipe, 0.0 )

% note, case is axisymmetric

MARKER_SYM= ( symmetry )

AXISYMMETRIC= YES

%

SPECIFIED_INLET_PROFILE= YES

INLET_MATCHING_TOLERANCE=1e-4

INLET_FILENAME= inlet.dat

INC_INLET_TYPE= VELOCITY_INLET

INC_INLET_DAMPING= 0.1

MARKER_INLET= ( inlet, 673, 40.0, 1.0, 0.0, 0.0)

MARKER_INLET_TURBULENT = (inlet, 0.10, 15)

MARKER_INLET_SPECIES= (inlet, 0.0)

%

INC_OUTLET_TYPE= PRESSURE_OUTLET

INC_OUTLET_DAMPING= 0.1

MARKER_OUTLET= ( outlet, 0.0 )

%

% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%

%

NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES

%

CFL_NUMBER= 10.00

CFL_REDUCTION_SPECIES= 1.0

CFL_REDUCTION_TURB= 1.0

CFL_ADAPT= YES

CFL_ADAPT_PARAM= ( 0.95, 1.01, 1.0, 250, 1.0e-4, 0)

%

ITER= 1

%

% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%

%

LINEAR_SOLVER= FGMRES

LINEAR_SOLVER_PREC= ILU

LINEAR_SOLVER_ERROR= 1E-12

LINEAR_SOLVER_ITER= 10

% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%

%

CONV_NUM_METHOD_FLOW= FDS

MUSCL_FLOW= NO

SLOPE_LIMITER_FLOW = NONE

TIME_DISCRE_FLOW= EULER_IMPLICIT

%

% -------------------- SCALAR TRANSPORT ---------------------------------------%

%

KIND_SCALAR_MODEL= SPECIES_TRANSPORT

%DIFFUSIVITY_MODEL= CONSTANT_DIFFUSIVITY

DIFFUSIVITY_MODEL= CONSTANT_SCHMIDT

%DIFFUSIVITY_MODEL= CONSTANT_LEWIS

SCHMIDT_NUMBER_LAMINAR= 1.0

CONSTANT_LEWIS_NUMBER= 1.0 1.0

DIFFUSIVITY_CONSTANT= 5.0e-5

% according to the paper

SCHMIDT_NUMBER_TURBULENT= 0.7

%

CONV_NUM_METHOD_SPECIES= BOUNDED_SCALAR

MUSCL_SPECIES= NO

SLOPE_LIMITER_SPECIES = NONE

%

TIME_DISCRE_SPECIES= EULER_IMPLICIT

%

SPECIES_INIT= 0.0

SPECIES_CLIPPING= YES

SPECIES_CLIPPING_MIN= 0.0

SPECIES_CLIPPING_MAX= 1.0

%

% -------------------- TURBULENT TRANSPORT ---------------------------------------%

%

CONV_NUM_METHOD_TURB= BOUNDED_SCALAR

MUSCL_TURB= NO

%

% --------------------------- CONVERGENCE PARAMETERS --------------------------%

%

CONV_FIELD= RMS_PRESSURE, RMS_VELOCITY-X, RMS_VELOCITY-Y, RMS_TKE, RMS_SPECIES

CONV_RESIDUAL_MINVAL= -18

CONV_STARTITER= 10

%

% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%

%

MESH_FILENAME= psi.su2

%

SCREEN_OUTPUT= INNER_ITER WALL_TIME \

RMS_PRESSURE RMS_VELOCITY-X RMS_VELOCITY-Y RMS_TKE RMS_DISSIPATION RMS_SPECIES_0

SCREEN_WRT_FREQ_INNER= 1

%

HISTORY_OUTPUT= ITER RMS_RES LINSOL SPECIES_COEFF SPECIES_COEFF_SURF

CONV_FILENAME= history

MARKER_ANALYZE= gas_inlet, air_axial_inlet, outlet

MARKER_ANALYZE_AVERAGE= AREA

%

OUTPUT_FILES= RESTART, RESTART_ASCII, PARAVIEW_MULTIBLOCK

VOLUME_OUTPUT= RESIDUAL, PRIMITIVE, SPECIES_UDS_0

OUTPUT_WRT_FREQ= 100

%

READ_BINARY_RESTART= YES

RESTART_FILENAME= restart

SOLUTION_FILENAME= solution

%

WRT_PERFORMANCE= YES

PYTHON_CUSTOM_SOURCE= YES