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[WIP] add axisymmetric jet case #2335

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[WIP] add axisymmetric jet case #2335

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dc4faeb
add axisymmetric jet case
bigfooted Aug 7, 2024
2b42bfd
add axisymmetric jet case, SA
bigfooted Aug 7, 2024
0a1d540
Merge branch 'develop' into testcase_axisymmetric_jet
bigfooted Aug 22, 2024
9945d97
Merge branch 'develop' into testcase_axisymmetric_jet
bigfooted Sep 5, 2024
6ec814a
Merge branch 'develop' into testcase_axisymmetric_jet
bigfooted Sep 25, 2024
8c4fa60
Merge branch 'develop' into testcase_axisymmetric_jet
bigfooted Oct 4, 2024
ecc6331
Merge branch 'develop' into testcase_axisymmetric_jet
bigfooted Oct 9, 2024
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16 changes: 16 additions & 0 deletions TestCases/vandv.py
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Original file line number Diff line number Diff line change
Expand Up @@ -89,6 +89,22 @@ def main():
### Incompressible RANS ###
##########################

# axisymmetric round jet (sst)
jet_sst = TestCase('jet_sst')
jet_sst.cfg_dir = "vandv/inc_rans/jet"
jet_sst.cfg_file = "config_sst.cfg"
jet_sst.test_iter = 20
jet_sst.test_vals = [-10.806343, -10.326374, -10.559106, -10.432754, -13.517105, 0.050962, 2.828563, 1.317849, -0.228843]
test_list.append(jet_sst)

# axisymmetric round jet (sa)
jet_sst = TestCase('jet_sa')
jet_sst.cfg_dir = "vandv/inc_rans/jet"
jet_sst.cfg_file = "config_sa.cfg"
jet_sst.test_iter = 20
jet_sst.test_vals = [-10.806343, -10.326374, -10.559106, -10.432754, -13.517105, 0.050962, 2.828563, 1.317849, -0.228843]
test_list.append(jet_sa)

# Sandia jet - sst-v2003m
sandiajet_sst = TestCase('sandiajet_sst')
sandiajet_sst.cfg_dir = "vandv/species_transport/sandia_jet"
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167 changes: 167 additions & 0 deletions TestCases/vandv/inc_rans/jet/jet_sa.cfg
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Original file line number Diff line number Diff line change
@@ -0,0 +1,167 @@
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% SU2 configuration file %
% Case description: Turbulent axisymmetric jet %
% Author: Nijso Beishuizen %
% Institution: SU2 Foundation %
% Date: 2024.01.01 %
% File Version 8.0.1 "Harrier" %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
SOLVER= INC_RANS
%
KIND_TURB_MODEL= SA
SA_OPTIONS= NONE
%
RESTART_SOL= YES

%
% --------------------------- VISCOSITY MODEL ---------------------------------%
VISCOSITY_MODEL= CONSTANT_VISCOSITY
MU_CONSTANT= 0.001

CONDUCTIVITY_MODEL= CONSTANT_CONDUCTIVITY
THERMAL_CONDUCTIVITY_CONSTANT= 0.6
TURBULENT_CONDUCTIVITY_MODEL= NONE

% ---------------- INCOMPRESSIBLE FLOW CONDITION DEFINITION -------------------%
INC_NONDIM= DIMENSIONAL
INC_DENSITY_MODEL= CONSTANT
INC_DENSITY_INIT= 1000.0

FLUID_MODEL= CONSTANT_DENSITY
SPECIFIC_HEAT_CP= 1000.0
INC_TEMPERATURE_INIT= 300.00
INC_ENERGY_EQUATION= NO
INC_VELOCITY_INIT= (0.5, 0.0, 0.0 )
INC_INLET_TYPE= VELOCITY_INLET, VELOCITY_INLET
INC_OUTLET_TYPE= PRESSURE_OUTLET

FREESTREAM_DENSITY= 1000.0
FREESTREAM_VISCOSITY= 0.001
FREESTREAM_VELOCITY= (0.5, 0.0, 0.0)
% ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------%
%
%
% Free-stream temperature (288.15 K by default)
FREESTREAM_TEMPERATURE= 300.0
%
% Reynolds number (non-dimensional, based on the free-stream values)
REYNOLDS_NUMBER= 2000.0
%
% Reynolds length (in meters)
REYNOLDS_LENGTH= 0.001

% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
%
% Reference origin for moment computation
REF_ORIGIN_MOMENT_X = 0.25
REF_ORIGIN_MOMENT_Y = 0.00
REF_ORIGIN_MOMENT_Z = 0.00
%
% Reference length for pitching, rolling, and yawing non-dimensional moment
REF_LENGTH= 0.001
%
% Reference area for force coefficients (0 implies automatic calculation)
REF_AREA= 0.001

% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
%
AXISYMMETRIC= YES
%
MARKER_INLET= ( inlet_jet, 300.0, 56.2, 1.0, 0.0, 0.0,inlet_coflow,300.0,0.5,1.0,0.0,0.0 )
%
MARKER_OUTLET= ( outlet, 0.0)
MARKER_HEATFLUX=(wall_edge,0.0, wall, 0.0, freestream, 0.0)
MARKER_FAR= (freestream)
%
MARKER_SYM= ( symmetry )
%
MARKER_INLET_TURBULENT= ( inlet_jet, 0.02,10, inlet_coflow, 0.02,10)
% Control lower limit constants of the SST model (C*phi_infinity)
LOWER_LIMIT_K_FACTOR= 1e-20
LOWER_LIMIT_OMEGA_FACTOR= 1e-6

% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
%
NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
CFL_NUMBER=100
CFL_ADAPT= NO
CFL_ADAPT_PARAM= ( 0.95, 1.01, 1.0, 200.0, 0.001 )
ITER= 99999
INC_INLET_DAMPING=0.01
INC_OUTLET_DAMPING= 0.01
% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
%
VENKAT_LIMITER_COEFF= 0.1
ADJ_SHARP_LIMITER_COEFF= 3.0
REF_SHARP_EDGES= 3.0
SENS_REMOVE_SHARP= NO

% -------------------------- MULTIGRID PARAMETERS -----------------------------%
%
MGLEVEL= 0
%
% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
CONV_NUM_METHOD_FLOW= FDS
MUSCL_FLOW= NO
SLOPE_LIMITER_FLOW= NONE
JST_SENSOR_COEFF= ( 0.5, 0.02 )
TIME_DISCRE_FLOW= EULER_IMPLICIT

% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
%
CONV_NUM_METHOD_TURB= SCALAR_UPWIND
MUSCL_TURB= NO
SLOPE_LIMITER_TURB= VENKATAKRISHNAN
TIME_DISCRE_TURB= EULER_IMPLICIT
% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
%
LINEAR_SOLVER= FGMRES
LINEAR_SOLVER_PREC= ILU
LINEAR_SOLVER_ERROR= 1E-6
LINEAR_SOLVER_ITER= 5

% --------------------------- CONVERGENCE PARAMETERS --------------------------%
%
CONV_RESIDUAL_MINVAL= -15
CONV_STARTITER= 10
CONV_CAUCHY_ELEMS= 100
CONV_CAUCHY_EPS= 1E-6
%

% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
%
MESH_FILENAME= jet_inlet_medium.su2
%
MESH_FORMAT= SU2
%
MESH_OUT_FILENAME= mesh_out.su2
%
SOLUTION_FILENAME= solution_flow_sa.dat
%
SOLUTION_ADJ_FILENAME= solution_adj.dat
%
TABULAR_FORMAT= CSV
%
CONV_FILENAME= history
%
RESTART_FILENAME= restart_flow_sa.dat
%
VOLUME_FILENAME= flow
%
%
% Output file surface flow coefficient (w/o extension)
SURFACE_FILENAME= surface_flow
%
% Writing solution file frequency
OUTPUT_WRT_FREQ= 100
%
%
SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_PRESSURE, RMS_MOMENTUM-X, RMS_VELOCITY-X, RMS_VELOCITY-Y, RMS_TKE, RMS_DISSIPATION, LINSOL_ITER, LINSOL_RESIDUAL, AVG_CFL)
OUTPUT_FILES= RESTART, PARAVIEW_MULTIBLOCK
VOLUME_OUTPUT= (PRIMITIVE,SOLUTION,RESIDUAL)
155 changes: 155 additions & 0 deletions TestCases/vandv/inc_rans/jet/jet_sst.cfg
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Original file line number Diff line number Diff line change
@@ -0,0 +1,155 @@
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% SU2 configuration file %
% Case description: Turbulent axisymmetric jet %
% Author: Nijso Beishuizen %
% Institution: SU2 Foundation %
% Date: 2024.01.01 %
% File Version 8.0.1 "Harrier" %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
SOLVER= INC_RANS
%
KIND_TURB_MODEL= SST
SST_OPTIONS= V2003m
%
RESTART_SOL= YES

% --------------------------- VISCOSITY MODEL ---------------------------------%
%
VISCOSITY_MODEL= CONSTANT_VISCOSITY
MU_CONSTANT= 0.001

CONDUCTIVITY_MODEL= CONSTANT_CONDUCTIVITY
THERMAL_CONDUCTIVITY_CONSTANT= 0.6
TURBULENT_CONDUCTIVITY_MODEL= NONE

% ---------------- INCOMPRESSIBLE FLOW CONDITION DEFINITION -------------------%
%
INC_NONDIM= DIMENSIONAL
INC_DENSITY_MODEL= CONSTANT
INC_DENSITY_INIT= 1000.0

FLUID_MODEL= CONSTANT_DENSITY
SPECIFIC_HEAT_CP= 1000.0
INC_TEMPERATURE_INIT= 300.00
INC_ENERGY_EQUATION= NO
INC_VELOCITY_INIT= (0.5, 0.0, 0.0 )
INC_INLET_TYPE= VELOCITY_INLET, VELOCITY_INLET
INC_OUTLET_TYPE= PRESSURE_OUTLET

% ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------%
%
FREESTREAM_TEMPERATURE= 300.0
FREESTREAM_DENSITY= 1000.0
FREESTREAM_VISCOSITY= 0.001
FREESTREAM_VELOCITY= (0.5, 0.0, 0.0)

% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
%
REF_ORIGIN_MOMENT_X = 0.25
REF_ORIGIN_MOMENT_Y = 0.00
REF_ORIGIN_MOMENT_Z = 0.00
REF_LENGTH= 0.001
REF_AREA= 0.001

% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
%
AXISYMMETRIC= YES
%
MARKER_INLET= ( inlet_jet, 300.0, 56.2, 1.0, 0.0, 0.0,inlet_coflow,300.0,0.5,1.0,0.0,0.0 )
%
MARKER_OUTLET= ( outlet, 0.0)
MARKER_HEATFLUX=(wall_edge,0.0, wall, 0.0, freestream, 0.0)
MARKER_FAR= (freestream)
%
MARKER_SYM= ( symmetry )
%
MARKER_INLET_TURBULENT= ( inlet_jet, 0.02,10, inlet_coflow, 0.02,10)

% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
%
NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
CFL_NUMBER=50
CFL_ADAPT= YES
CFL_ADAPT_PARAM= ( 0.95, 1.01, 1.0, 200.0, 0.001 )
ITER= 99999
INC_INLET_DAMPING=0.01
INC_OUTLET_DAMPING= 0.01

% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
%
VENKAT_LIMITER_COEFF= 0.1
ADJ_SHARP_LIMITER_COEFF= 3.0
REF_SHARP_EDGES= 3.0
SENS_REMOVE_SHARP= NO

% -------------------------- MULTIGRID PARAMETERS -----------------------------%
%
MGLEVEL= 0

% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
CONV_NUM_METHOD_FLOW= FDS
MUSCL_FLOW= NO
SLOPE_LIMITER_FLOW= NONE
JST_SENSOR_COEFF= ( 0.5, 0.02 )
TIME_DISCRE_FLOW= EULER_IMPLICIT

% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
%
CONV_NUM_METHOD_TURB= SCALAR_UPWIND
MUSCL_TURB= NO
SLOPE_LIMITER_TURB= VENKATAKRISHNAN
TIME_DISCRE_TURB= EULER_IMPLICIT
% Control lower limit constants of the SST model (C*phi_infinity)
LOWER_LIMIT_K_FACTOR= 1e-20
LOWER_LIMIT_OMEGA_FACTOR= 1e-6

% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
%
LINEAR_SOLVER= FGMRES
LINEAR_SOLVER_PREC= ILU
LINEAR_SOLVER_ERROR= 1E-6
LINEAR_SOLVER_ITER= 5

% --------------------------- CONVERGENCE PARAMETERS --------------------------%
%
CONV_RESIDUAL_MINVAL= -15
CONV_STARTITER= 10
CONV_CAUCHY_ELEMS= 100
CONV_CAUCHY_EPS= 1E-6

% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
%
MESH_FILENAME= jet_inlet_coarse.su2
%
MESH_FORMAT= SU2
%
MESH_OUT_FILENAME= mesh_out.su2
%
SOLUTION_FILENAME= solution_flow.dat
%
SOLUTION_ADJ_FILENAME= solution_adj.dat
%
TABULAR_FORMAT= CSV
%
CONV_FILENAME= history
%
RESTART_FILENAME= restart_flow.dat
%
VOLUME_FILENAME= flow
%
% Output file surface flow coefficient (w/o extension)
SURFACE_FILENAME= surface_flow
%
% Writing solution file frequency
OUTPUT_WRT_FREQ= 100
%
%
SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_PRESSURE, RMS_MOMENTUM-X, RMS_VELOCITY-X, RMS_VELOCITY-Y, RMS_TKE, RMS_DISSIPATION, LINSOL_ITER, LINSOL_RESIDUAL, AVG_CFL)
OUTPUT_FILES= (RESTART, PARAVIEW_MULTIBLOCK)
VOLUME_OUTPUT= (PRIMITIVE, SOLUTION, RESIDUAL)