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Merge pull request #1784 from su2code/fix_sst_axisymmetry
Fix axisymmetric divergence for SST production
2 parents 9f76df4 + 70d3cbd commit 7f96fbe

27 files changed

+490
-1630
lines changed

‎.github/workflows/regression.yml

+1-1
Original file line numberDiff line numberDiff line change
@@ -128,7 +128,7 @@ jobs:
128128
uses: docker://ghcr.io/su2code/su2/test-su2:220614-1237
129129
with:
130130
# -t <Tutorials-branch> -c <Testcases-branch>
131-
args: -b ${{github.ref}} -t develop -c develop_tmp -s ${{matrix.testscript}}
131+
args: -b ${{github.ref}} -t develop -c develop -s ${{matrix.testscript}}
132132
- name: Cleanup
133133
uses: docker://ghcr.io/su2code/su2/test-su2:220614-1237
134134
with:

‎SU2_CFD/include/numerics/turbulent/turb_sources.hpp

+17-13
Original file line numberDiff line numberDiff line change
@@ -610,14 +610,11 @@ class CSourcePieceWise_TurbSST final : public CNumerics {
610610
}
611611

612612
/*!
613-
* \brief Add contribution due to axisymmetric formulation to 2D residual
613+
* \brief Add contribution from convection and diffusion due to axisymmetric formulation to 2D residual
614614
*/
615-
inline void ResidualAxisymmetric(su2double alfa_blended, su2double zeta) {
615+
inline void ResidualAxisymmetricConvectionDiffusion(su2double alfa_blended, su2double zeta) {
616616
if (Coord_i[1] < EPS) return;
617617

618-
AD::SetPreaccIn(Coord_i[1]);
619-
AD::SetPreaccIn(V_i[idx.Velocity() + 1]);
620-
621618
const su2double yinv = 1.0 / Coord_i[1];
622619
const su2double rhov = Density_i * V_i[idx.Velocity() + 1];
623620
const su2double& k = ScalarVar_i[0];
@@ -627,18 +624,20 @@ class CSourcePieceWise_TurbSST final : public CNumerics {
627624
const su2double sigma_k_i = F1_i * sigma_k_1 + (1.0 - F1_i) * sigma_k_2;
628625
const su2double sigma_w_i = F1_i * sigma_w_1 + (1.0 - F1_i) * sigma_w_2;
629626

630-
/*--- Production ---*/
631-
const su2double pk_axi = max(
632-
0.0, 2.0 / 3.0 * rhov * k * ((2.0 * yinv * V_i[idx.Velocity() + 1] - PrimVar_Grad_i[idx.Velocity()+1][1] - PrimVar_Grad_i[idx.Velocity()][0]) / zeta - 1.0));
633-
const su2double pw_axi = alfa_blended * zeta / k * pk_axi;
634-
635627
/*--- Convection-Diffusion ---*/
636628
const su2double cdk_axi = rhov * k - (Laminar_Viscosity_i + sigma_k_i * Eddy_Viscosity_i) * ScalarVar_Grad_i[0][1];
637629
const su2double cdw_axi = rhov * w - (Laminar_Viscosity_i + sigma_w_i * Eddy_Viscosity_i) * ScalarVar_Grad_i[1][1];
638630

639631
/*--- Add terms to the residuals ---*/
640-
Residual[0] += yinv * Volume * (pk_axi - cdk_axi);
641-
Residual[1] += yinv * Volume * (pw_axi - cdw_axi);
632+
633+
Residual[0] -= yinv * Volume * cdk_axi;
634+
Residual[1] -= yinv * Volume * cdw_axi;
635+
636+
Jacobian_i[0][0] -= yinv * Volume * rhov;
637+
Jacobian_i[0][1] -= 0.0;
638+
Jacobian_i[1][0] -= 0.0;
639+
Jacobian_i[1][1] -= yinv * Volume * rhov;
640+
642641
}
643642

644643
public:
@@ -716,6 +715,7 @@ class CSourcePieceWise_TurbSST final : public CNumerics {
716715
AD::SetPreaccIn(PrimVar_Grad_i, nDim + idx.Velocity(), nDim);
717716
AD::SetPreaccIn(Vorticity_i, 3);
718717
AD::SetPreaccIn(V_i[idx.Density()], V_i[idx.LaminarViscosity()], V_i[idx.EddyViscosity()]);
718+
AD::SetPreaccIn(V_i[idx.Velocity() + 1]);
719719

720720
Density_i = V_i[idx.Density()];
721721
Laminar_Viscosity_i = V_i[idx.LaminarViscosity()];
@@ -745,6 +745,10 @@ class CSourcePieceWise_TurbSST final : public CNumerics {
745745
su2double diverg = 0.0;
746746
for (unsigned short iDim = 0; iDim < nDim; iDim++)
747747
diverg += PrimVar_Grad_i[iDim + idx.Velocity()][iDim];
748+
if (axisymmetric && Coord_i[1] > EPS) {
749+
AD::SetPreaccIn(Coord_i[1]);
750+
diverg += V_i[idx.Velocity() + 1] / Coord_i[1];
751+
}
748752

749753
/*--- If using UQ methodolgy, calculate production using perturbed Reynolds stress matrix ---*/
750754

@@ -836,7 +840,7 @@ class CSourcePieceWise_TurbSST final : public CNumerics {
836840

837841
/*--- Contribution due to 2D axisymmetric formulation ---*/
838842

839-
if (axisymmetric) ResidualAxisymmetric(alfa_blended, zeta);
843+
if (axisymmetric) ResidualAxisymmetricConvectionDiffusion(alfa_blended, zeta);
840844

841845
/*--- Implicit part ---*/
842846

‎SU2_CFD/include/solvers/CFVMFlowSolverBase.hpp

+1-1
Original file line numberDiff line numberDiff line change
@@ -1004,7 +1004,7 @@ class CFVMFlowSolverBase : public CSolver {
10041004
/*!
10051005
* \brief Evaluate the vorticity and strain rate magnitude.
10061006
*/
1007-
void ComputeVorticityAndStrainMag(const CConfig& config, unsigned short iMesh);
1007+
void ComputeVorticityAndStrainMag(const CConfig& config, const CGeometry *geometry, unsigned short iMesh);
10081008

10091009
/*!
10101010
* \brief Destructor.

‎SU2_CFD/include/solvers/CFVMFlowSolverBase.inl

+7-9
Original file line numberDiff line numberDiff line change
@@ -584,7 +584,7 @@ void CFVMFlowSolverBase<V, R>::ImplicitEuler_Iteration(CGeometry *geometry, CSol
584584
}
585585

586586
template <class V, ENUM_REGIME R>
587-
void CFVMFlowSolverBase<V, R>::ComputeVorticityAndStrainMag(const CConfig& config, unsigned short iMesh) {
587+
void CFVMFlowSolverBase<V, R>::ComputeVorticityAndStrainMag(const CConfig& config, const CGeometry *geometry, unsigned short iMesh) {
588588

589589
auto& StrainMag = nodes->GetStrainMag();
590590

@@ -611,23 +611,21 @@ void CFVMFlowSolverBase<V, R>::ComputeVorticityAndStrainMag(const CConfig& confi
611611

612612
/*--- Strain Magnitude ---*/
613613

614+
const su2double vy = nodes->GetVelocity(iPoint, 1);
615+
const su2double y = geometry->nodes->GetCoord(iPoint, 1);
614616
AD::StartPreacc();
615617
AD::SetPreaccIn(VelocityGradient, nDim, nDim);
616-
617-
su2double Div = 0.0;
618-
for (unsigned long iDim = 0; iDim < nDim; iDim++)
619-
Div += VelocityGradient(iDim, iDim);
620-
Div /= 3.0;
618+
AD::SetPreaccIn(vy, y);
621619

622620
StrainMag(iPoint) = 0.0;
623621

624622
/*--- Add diagonal part ---*/
625623

626624
for (unsigned long iDim = 0; iDim < nDim; iDim++) {
627-
StrainMag(iPoint) += pow(VelocityGradient(iDim, iDim) - Div, 2);
625+
StrainMag(iPoint) += pow(VelocityGradient(iDim, iDim), 2);
628626
}
629-
if (nDim == 2) {
630-
StrainMag(iPoint) += pow(Div, 2);
627+
if (config.GetAxisymmetric() && y > EPS) {
628+
StrainMag(iPoint) += pow(vy / y, 2);
631629
}
632630

633631
/*--- Add off diagonals ---*/

‎SU2_CFD/include/variables/CVariable.hpp

+1-34
Original file line numberDiff line numberDiff line change
@@ -1133,20 +1133,6 @@ class CVariable {
11331133
*/
11341134
inline virtual su2double GetThermalConductivity_ve(unsigned long iPoint) const { return 0.0; }
11351135

1136-
/*!
1137-
* \brief A virtual member.
1138-
* \param[in] iPoint - Point index.
1139-
* \return Sets separation intermittency
1140-
*/
1141-
inline virtual void SetGammaSep(unsigned long iPoint, su2double gamma_sep) {}
1142-
1143-
/*!
1144-
* \brief A virtual member.
1145-
* \param[in] iPoint - Point index.
1146-
* \return Sets separation intermittency
1147-
*/
1148-
inline virtual void SetGammaEff(unsigned long iPoint) {}
1149-
11501136
/*!
11511137
* \brief A virtual member.
11521138
* \param[in] iPoint - Point index.
@@ -1408,29 +1394,10 @@ class CVariable {
14081394
*/
14091395
inline virtual su2double *GetdTvedU(unsigned long iPoint) { return nullptr; }
14101396

1411-
/*!
1412-
* \brief A virtual member.
1413-
* \param[in] val_velocity - Value of the velocity.
1414-
* \param[in] Gamma - Ratio of Specific heats
1415-
*/
1416-
inline virtual void SetDeltaPressure(unsigned long iPoint, const su2double *val_velocity, su2double Gamma) {}
1417-
1418-
/*!
1419-
* \brief A virtual member.
1420-
* \param[in] Gamma - Ratio of specific heats.
1421-
*/
1422-
inline virtual bool SetSoundSpeed(unsigned long iPoint, su2double Gamma) { return false; }
1423-
1424-
/*!
1425-
* \brief A virtual member.
1426-
* \param[in] config - Configuration parameters.
1427-
*/
1428-
inline virtual bool SetSoundSpeed(unsigned long iPoint, CConfig *config) { return false; }
1429-
14301397
/*!
14311398
* \brief A virtual member.
14321399
*/
1433-
inline virtual bool SetSoundSpeed(unsigned long iPoint) { return false; }
1400+
inline virtual bool SetSoundSpeed(unsigned long iPoint, su2double soundspeed2) { return false; }
14341401

14351402
/*!
14361403
* \brief A virtual member.

‎SU2_CFD/src/solvers/CIncNSSolver.cpp

+1-1
Original file line numberDiff line numberDiff line change
@@ -102,7 +102,7 @@ void CIncNSSolver::Preprocessing(CGeometry *geometry, CSolver **solver_container
102102
SetPrimitive_Limiter(geometry, config);
103103
}
104104

105-
ComputeVorticityAndStrainMag(*config, iMesh);
105+
ComputeVorticityAndStrainMag(*config, geometry, iMesh);
106106

107107
/*--- Compute the TauWall from the wall functions ---*/
108108

‎SU2_CFD/src/solvers/CNEMONSSolver.cpp

+1-1
Original file line numberDiff line numberDiff line change
@@ -98,7 +98,7 @@ void CNEMONSSolver::Preprocessing(CGeometry *geometry, CSolver **solver_containe
9898

9999
/*--- Compute vorticity and strain mag. ---*/
100100

101-
ComputeVorticityAndStrainMag(*config, iMesh);
101+
ComputeVorticityAndStrainMag(*config, geometry, iMesh);
102102

103103
/*--- Compute the TauWall from the wall functions ---*/
104104

‎SU2_CFD/src/solvers/CNSSolver.cpp

+1-1
Original file line numberDiff line numberDiff line change
@@ -116,7 +116,7 @@ void CNSSolver::Preprocessing(CGeometry *geometry, CSolver **solver_container, C
116116
SetPrimitive_Limiter(geometry, config);
117117
}
118118

119-
ComputeVorticityAndStrainMag(*config, iMesh);
119+
ComputeVorticityAndStrainMag(*config, geometry, iMesh);
120120

121121
/*--- Compute the TauWall from the wall functions ---*/
122122

‎TestCases/axisymmetric_rans/air_nozzle/air_nozzle.cfg ‎TestCases/axisymmetric_rans/air_nozzle/air_nozzle_restart.cfg

+2-1
Original file line numberDiff line numberDiff line change
@@ -86,7 +86,7 @@ CFL_REDUCTION_TURB= 1.0
8686
%
8787
% --------------------------- CONVERGENCE PARAMETERS --------------------------%
8888
%
89-
ITER= 1000
89+
ITER= 3000
9090
CONV_RESIDUAL_MINVAL= -12
9191
CONV_STARTITER= 10
9292
%
@@ -95,6 +95,7 @@ CONV_STARTITER= 10
9595
MESH_FILENAME= nozzle.su2
9696
%
9797
SOLUTION_FILENAME= solution_flow.dat
98+
RESTART_FILENAME= restart_flow.dat
9899
OUTPUT_WRT_FREQ= 1000
99100
%
100101
% Note: This cfg is used for a primal and adjoint Testcase, therefore both residuals are present here.

‎TestCases/hybrid_regression.py

+31-50
Original file line numberDiff line numberDiff line change
@@ -166,15 +166,15 @@ def main():
166166
rae2822_sst.cfg_dir = "rans/rae2822"
167167
rae2822_sst.cfg_file = "turb_SST_RAE2822.cfg"
168168
rae2822_sst.test_iter = 20
169-
rae2822_sst.test_vals = [-0.510635, 4.871104, 0.811904, 0.061614, -82395.000000]
169+
rae2822_sst.test_vals = [-0.510634, 4.869669, 0.811906, 0.061614, -82395.000000]
170170
test_list.append(rae2822_sst)
171171

172172
# RAE2822 SST_SUST
173173
rae2822_sst_sust = TestCase('rae2822_sst_sust')
174174
rae2822_sst_sust.cfg_dir = "rans/rae2822"
175175
rae2822_sst_sust.cfg_file = "turb_SST_SUST_RAE2822.cfg"
176176
rae2822_sst_sust.test_iter = 20
177-
rae2822_sst_sust.test_vals = [-2.430589, 4.871104, 0.811903, 0.061614]
177+
rae2822_sst_sust.test_vals = [-2.420843, 4.869669, 0.811906, 0.061614]
178178
test_list.append(rae2822_sst_sust)
179179

180180
# Flat plate
@@ -207,7 +207,7 @@ def main():
207207
turb_naca0012_sst.cfg_dir = "rans/naca0012"
208208
turb_naca0012_sst.cfg_file = "turb_NACA0012_sst.cfg"
209209
turb_naca0012_sst.test_iter = 10
210-
turb_naca0012_sst.test_vals = [-11.450472, -12.797872, -5.863655, 1.049989, 0.019163, -1.856265, -38.694000]
210+
turb_naca0012_sst.test_vals = [-11.418415, -12.801780, -5.864804, 1.049990, 0.019163, -1.669899, -38.695000]
211211
turb_naca0012_sst.test_vals_aarch64 = [-11.450473, -12.797872, -5.863655, 1.049989, 0.019163, -1.856266, -38.694000]
212212
test_list.append(turb_naca0012_sst)
213213

@@ -216,7 +216,7 @@ def main():
216216
turb_naca0012_sst_sust.cfg_dir = "rans/naca0012"
217217
turb_naca0012_sst_sust.cfg_file = "turb_NACA0012_sst_sust.cfg"
218218
turb_naca0012_sst_sust.test_iter = 10
219-
turb_naca0012_sst_sust.test_vals = [-11.367052, -12.640670, -5.746919, 1.005233, 0.019017, -1.913902]
219+
turb_naca0012_sst_sust.test_vals = [-11.361657, -12.642245, -5.747099, 1.005234, 0.019017, -1.573783]
220220
turb_naca0012_sst_sust.test_vals_aarch64 = [-11.367052, -12.640670, -5.746919, 1.005233, 0.019017, -1.913907]
221221
test_list.append(turb_naca0012_sst_sust)
222222

@@ -225,7 +225,7 @@ def main():
225225
turb_naca0012_sst_fixedvalues.cfg_dir = "rans/naca0012"
226226
turb_naca0012_sst_fixedvalues.cfg_file = "turb_NACA0012_sst_fixedvalues.cfg"
227227
turb_naca0012_sst_fixedvalues.test_iter = 10
228-
turb_naca0012_sst_fixedvalues.test_vals = [-5.192502, -9.575898, -1.568269, 1.022571, 0.040527, -2.384329]
228+
turb_naca0012_sst_fixedvalues.test_vals = [-5.192502, -9.575351, -1.568269, 1.022571, 0.040527, -2.384334]
229229
turb_naca0012_sst_fixedvalues.test_vals_aarch64 = [-5.192501, -9.575897, -1.568269, 1.022571, 0.040527, -2.384327]
230230
test_list.append(turb_naca0012_sst_fixedvalues)
231231

@@ -250,13 +250,13 @@ def main():
250250
#######################################
251251

252252
# Axisymmetric air nozzle (transonic)
253-
axi_rans_air_nozzle = TestCase('axi_rans_air_nozzle')
254-
axi_rans_air_nozzle.cfg_dir = "axisymmetric_rans/air_nozzle"
255-
axi_rans_air_nozzle.cfg_file = "air_nozzle.cfg"
256-
axi_rans_air_nozzle.test_iter = 10
257-
axi_rans_air_nozzle.test_vals = [-12.093553, -6.630383, -8.798737, -2.399130, -1938.200000]
258-
axi_rans_air_nozzle.test_vals_aarch64 = [-12.093539, -6.630357, -8.798732, -2.399130, -1938.200000]
259-
test_list.append(axi_rans_air_nozzle)
253+
axi_rans_air_nozzle_restart = TestCase('axi_rans_air_nozzle_restart')
254+
axi_rans_air_nozzle_restart.cfg_dir = "axisymmetric_rans/air_nozzle"
255+
axi_rans_air_nozzle_restart.cfg_file = "air_nozzle_restart.cfg"
256+
axi_rans_air_nozzle_restart.test_iter = 10
257+
axi_rans_air_nozzle_restart.test_vals = [-12.094405, -6.649212, -8.899548, -2.491859, -1924.900000]
258+
axi_rans_air_nozzle_restart.test_vals_aarch64 = [-12.093539, -6.630357, -8.798732, -2.399130, -1938.200000]
259+
test_list.append(axi_rans_air_nozzle_restart)
260260

261261
#################################
262262
## Compressible RANS Restart ###
@@ -424,7 +424,7 @@ def main():
424424
inc_turb_naca0012_sst_sust.cfg_dir = "incomp_rans/naca0012"
425425
inc_turb_naca0012_sst_sust.cfg_file = "naca0012_SST_SUST.cfg"
426426
inc_turb_naca0012_sst_sust.test_iter = 20
427-
inc_turb_naca0012_sst_sust.test_vals = [-7.276424, 0.145860, 0.000003, 0.312011]
427+
inc_turb_naca0012_sst_sust.test_vals = [-7.274028, 0.145888, 0.000002, 0.312014]
428428
test_list.append(inc_turb_naca0012_sst_sust)
429429

430430
######################################
@@ -457,7 +457,7 @@ def main():
457457
square_cylinder.cfg_dir = "unsteady/square_cylinder"
458458
square_cylinder.cfg_file = "turb_square.cfg"
459459
square_cylinder.test_iter = 3
460-
square_cylinder.test_vals = [-2.558001, -1.162564, 0.066372, 1.399788, 2.220402, 1.399743, 2.218603, -0.453110]
460+
square_cylinder.test_vals = [-2.558128, -1.158062, 0.067932, 1.399788, 2.220402, 1.399743, 2.218603, -0.453110]
461461
square_cylinder.test_vals_aarch64 = [-2.558106, -1.162563, 0.066386, 1.399788, 2.220402, 1.399743, 2.218603, -0.453110]
462462
square_cylinder.unsteady = True
463463
test_list.append(square_cylinder)
@@ -534,53 +534,34 @@ def main():
534534
### Turbomachinery ###
535535
######################################
536536

537-
# Jones APU Turbocharger
538-
Jones_tc = TestCase('jones_turbocharger')
539-
Jones_tc.cfg_dir = "turbomachinery/APU_turbocharger"
540-
Jones_tc.cfg_file = "Jones.cfg"
541-
Jones_tc.test_iter = 5
542-
Jones_tc.test_vals = [-5.279930, 0.379651, 72.212100, 1.277439]
543-
Jones_tc.new_output = False
544-
test_list.append(Jones_tc)
545-
546537
# Jones APU Turbocharger restart
547-
Jones_tc_rst = TestCase('jones_turbocharger_restart')
548-
Jones_tc_rst.cfg_dir = "turbomachinery/APU_turbocharger"
549-
Jones_tc_rst.cfg_file = "Jones_rst.cfg"
550-
Jones_tc_rst.test_iter = 5
551-
Jones_tc_rst.test_vals = [-4.625251, -1.568824, 33.995140, 10.181940]
552-
Jones_tc_rst.new_output = False
553-
test_list.append(Jones_tc_rst)
538+
Jones_tc_restart = TestCase('jones_turbocharger_restart')
539+
Jones_tc_restart.cfg_dir = "turbomachinery/APU_turbocharger"
540+
Jones_tc_restart.cfg_file = "Jones_restart.cfg"
541+
Jones_tc_restart.test_iter = 5
542+
Jones_tc_restart.test_vals = [-10.691521, -7.643723, 85.827890, 2.277151]
543+
Jones_tc_restart.new_output = False
544+
test_list.append(Jones_tc_restart)
554545

555546
# 2D axial stage
556547
axial_stage2D = TestCase('axial_stage2D')
557548
axial_stage2D.cfg_dir = "turbomachinery/axial_stage_2D"
558549
axial_stage2D.cfg_file = "Axial_stage2D.cfg"
559550
axial_stage2D.test_iter = 20
560-
axial_stage2D.test_vals = [-1.933115, 5.365584, 73.354510, 0.925901]
551+
axial_stage2D.test_vals = [-1.937003, 5.338805, 73.357170, 0.915734]
561552
axial_stage2D.test_vals_aarch64 = [-1.933115, 5.365583, 73.354510, 0.925902]
562553
axial_stage2D.new_output = False
563554
test_list.append(axial_stage2D)
564555

565-
# 2D transonic stator
566-
transonic_stator = TestCase('transonic_stator')
567-
transonic_stator.cfg_dir = "turbomachinery/transonic_stator_2D"
568-
transonic_stator.cfg_file = "transonic_stator.cfg"
569-
transonic_stator.test_iter = 20
570-
transonic_stator.test_vals = [-0.565608, 5.833408, 96.476150, 0.062517]
571-
transonic_stator.test_vals_aarch64 = [-0.565610, 5.833410, 96.476160, 0.062517]
572-
transonic_stator.new_output = False
573-
test_list.append(transonic_stator)
574-
575556
# 2D transonic stator restart
576-
transonic_stator_rst = TestCase('transonic_stator_restart')
577-
transonic_stator_rst.cfg_dir = "turbomachinery/transonic_stator_2D"
578-
transonic_stator_rst.cfg_file = "transonic_stator_rst.cfg"
579-
transonic_stator_rst.test_iter = 20
580-
transonic_stator_rst.test_vals = [-6.619122, -0.615690, 5.002986, 0.002951]
581-
transonic_stator_rst.test_vals_aarch64 = [-6.619122, -0.615705, 5.002986, 0.002951]
582-
transonic_stator_rst.new_output = False
583-
test_list.append(transonic_stator_rst)
557+
transonic_stator_restart = TestCase('transonic_stator_restart')
558+
transonic_stator_restart.cfg_dir = "turbomachinery/transonic_stator_2D"
559+
transonic_stator_restart.cfg_file = "transonic_stator_restart.cfg"
560+
transonic_stator_restart.test_iter = 20
561+
transonic_stator_restart.test_vals = [-6.796363, -0.743837, 5.003453, 0.002946]
562+
transonic_stator_restart.test_vals_aarch64 = [-6.619122, -0.615705, 5.002986, 0.002951]
563+
transonic_stator_restart.new_output = False
564+
test_list.append(transonic_stator_restart)
584565

585566
######################################
586567
### Sliding Mesh ###
@@ -652,7 +633,7 @@ def main():
652633
bars_SST_2D.cfg_dir = "sliding_interface/bars_SST_2D"
653634
bars_SST_2D.cfg_file = "bars.cfg"
654635
bars_SST_2D.test_iter = 13
655-
bars_SST_2D.test_vals = [13.000000, -0.619686, -1.564595]
636+
bars_SST_2D.test_vals = [13.000000, -0.609170, -1.523885]
656637
bars_SST_2D.multizone = True
657638
test_list.append(bars_SST_2D)
658639

‎TestCases/hybrid_regression_AD.py

+1-1
Original file line numberDiff line numberDiff line change
@@ -193,7 +193,7 @@ def main():
193193
discadj_trans_stator.cfg_dir = "disc_adj_turbomachinery/transonic_stator_2D"
194194
discadj_trans_stator.cfg_file = "transonic_stator.cfg"
195195
discadj_trans_stator.test_iter = 79
196-
discadj_trans_stator.test_vals = [79.000000, -1.938806, -1.995540]
196+
discadj_trans_stator.test_vals = [79.000000, -1.938803, -1.981888]
197197
discadj_trans_stator.test_vals_aarch64 = [79.000000, -1.938809, -1.995540]
198198
test_list.append(discadj_trans_stator)
199199

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