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update vandv, update start+restart air_nozzle case
1 parent 170d534 commit 736ed1c

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Lines changed: 118 additions & 5 deletions

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‎TestCases/axisymmetric_rans/air_nozzle/air_nozzle.cfg‎

Lines changed: 3 additions & 2 deletions
Original file line numberDiff line numberDiff line change
@@ -12,7 +12,7 @@
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%
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SOLVER= RANS
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KIND_TURB_MODEL= SST
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RESTART_SOL= YES
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RESTART_SOL= NO
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%
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AXISYMMETRIC= YES
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%
@@ -94,7 +94,8 @@ CONV_STARTITER= 10
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%
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MESH_FILENAME= nozzle.su2
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%
97-
SOLUTION_FILENAME= solution_flow.dat
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SOLUTION_FILENAME= restart_flow.dat
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RESTART_FILENAME= restart_flow.dat
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OUTPUT_WRT_FREQ= 1000
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%
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% Note: This cfg is used for a primal and adjoint Testcase, therefore both residuals are present here.

‎TestCases/axisymmetric_rans/air_nozzle/air_nozzle_restart.cfg‎

Lines changed: 103 additions & 0 deletions
Original file line numberDiff line numberDiff line change
@@ -0,0 +1,103 @@
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: Axisymmetric supersonic converging-diverging air nozzle %
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% Author: Florian Dittmann %
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% Date: 2021.12.02 %
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% File Version 7.4.0 "Blackbird" %
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% %
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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%
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% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
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%
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SOLVER= RANS
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KIND_TURB_MODEL= SST
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RESTART_SOL= YES
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%
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AXISYMMETRIC= YES
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%
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% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
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%
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MACH_NUMBER= 1E-9
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%
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INIT_OPTION= TD_CONDITIONS
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%
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FREESTREAM_OPTION= TEMPERATURE_FS
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FREESTREAM_PRESSURE= 1400000
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FREESTREAM_TEMPERATURE= 373.15
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%
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REF_DIMENSIONALIZATION= DIMENSIONAL
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%
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% ---- IDEAL GAS, POLYTROPIC, VAN DER WAALS AND PENG ROBINSON CONSTANTS -------%
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%
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FLUID_MODEL= STANDARD_AIR
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%
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% --------------------------- VISCOSITY MODEL ---------------------------------%
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%
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VISCOSITY_MODEL= CONSTANT_VISCOSITY
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MU_CONSTANT= 1.716E-5
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%
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% --------------------------- THERMAL CONDUCTIVITY MODEL ----------------------%
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%
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CONDUCTIVITY_MODEL= CONSTANT_PRANDTL
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PRANDTL_LAM= 0.72
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PRANDTL_TURB= 0.90
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%
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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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%
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MARKER_HEATFLUX= ( WALL, 0.0 )
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MARKER_SYM= ( SYMMETRY )
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MARKER_RIEMANN= ( INFLOW, TOTAL_CONDITIONS_PT, 1400000.0, 373.15, 1.0, 0.0, 0.0, \
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OUTFLOW, STATIC_PRESSURE, 100000.0, 0.0, 0.0, 0.0, 0.0 )
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MARKER_MONITORING = (WALL)
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% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
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%
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NUM_METHOD_GRAD= GREEN_GAUSS
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CFL_NUMBER= 1000.0
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CFL_ADAPT= NO
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MAX_DELTA_TIME= 1E6
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OBJECTIVE_FUNCTION= DRAG
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%
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% ----------- SLOPE LIMITER AND DISSIPATION SENSOR DEFINITION -----------------%
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%
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MUSCL_FLOW= YES
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SLOPE_LIMITER_FLOW= NONE
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%
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% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
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%
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LINEAR_SOLVER= FGMRES
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LINEAR_SOLVER_PREC= ILU
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LINEAR_SOLVER_ILU_FILL_IN= 0
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LINEAR_SOLVER_ERROR= 0.01
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LINEAR_SOLVER_ITER= 10
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%
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% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
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%
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CONV_NUM_METHOD_FLOW= ROE
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ENTROPY_FIX_COEFF= 0.1
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TIME_DISCRE_FLOW= EULER_IMPLICIT
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%
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% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
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%
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CONV_NUM_METHOD_TURB= SCALAR_UPWIND
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TIME_DISCRE_TURB= EULER_IMPLICIT
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CFL_REDUCTION_TURB= 1.0
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%
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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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%
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ITER= 1000
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CONV_RESIDUAL_MINVAL= -12
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CONV_STARTITER= 10
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%
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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%
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MESH_FILENAME= nozzle.su2
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%
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SOLUTION_FILENAME= restart_flow.dat
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RESTART_FILENAME= restart_flow.dat
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OUTPUT_WRT_FREQ= 1000
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%
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% Note: This cfg is used for a primal and adjoint Testcase, therefore both residuals are present here.
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SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_ENERGY, RMS_TKE, RMS_DISSIPATION, TOTAL_HEATFLUX, \
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RMS_ADJ_DENSITY, RMS_ADJ_ENERGY, RMS_ADJ_TKE, RMS_ADJ_DISSIPATION, SENS_AOA, SENS_MACH)

‎TestCases/serial_regression.py‎

Lines changed: 12 additions & 3 deletions
Original file line numberDiff line numberDiff line change
@@ -348,10 +348,19 @@ def main():
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### Axisymmetric Compressible RANS ###
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#######################################
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# Axisymmetric air nozzle (transonic) start
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axi_rans_air_nozzle = TestCase('axi_rans_air_nozzle')
353+
axi_rans_air_nozzle.cfg_dir = "axisymmetric_rans/air_nozzle"
354+
axi_rans_air_nozzle.cfg_file = "air_nozzle.cfg"
355+
axi_rans_air_nozzle.test_iter = 20
356+
axi_rans_air_nozzle.test_vals = [-12.092891, -6.630495, -8.784840, -2.399099, -1938.200000]
357+
axi_rans_air_nozzle.tol = 0.0001
358+
test_list.append(axi_rans_air_nozzle)
359+
351360
# Axisymmetric air nozzle (transonic) restart
352-
axi_rans_air_nozzle_restart = TestCase('axi_rans_air_nozzle')
361+
axi_rans_air_nozzle_restart = TestCase('axi_rans_air_nozzle_restart')
353362
axi_rans_air_nozzle_restart.cfg_dir = "axisymmetric_rans/air_nozzle"
354-
axi_rans_air_nozzle_restart.cfg_file = "air_nozzle.cfg"
363+
axi_rans_air_nozzle_restart.cfg_file = "air_nozzle_restart.cfg"
355364
axi_rans_air_nozzle_restart.test_iter = 10
356365
axi_rans_air_nozzle_restart.test_vals = [-12.092891, -6.630495, -8.784840, -2.399099, -1938.200000]
357366
axi_rans_air_nozzle_restart.tol = 0.0001
@@ -937,7 +946,7 @@ def main():
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axial_stage2D.cfg_dir = "turbomachinery/axial_stage_2D"
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axial_stage2D.cfg_file = "Axial_stage2D.cfg"
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axial_stage2D.test_iter = 20
940-
axial_stage2D.test_vals = [-1.933127, 5.364763, 73.354550, 0.925896] #last 4 columns
949+
axial_stage2D.test_vals = [-1.937012, 5.338671, 73.357200, 0.915728] #last 4 columns
941950
axial_stage2D.new_output = False
942951
test_list.append(axial_stage2D)
943952

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