BC inlet for SA solver based on local conditions at the Inlet

Common/src/CConfig.cpp

@@ -5336,6 +5336,11 @@ void CConfig::SetPostprocessing(SU2_COMPONENT val_software, unsigned short val_i
         "The use of MARKER_INLET_TURBULENT requires the number of entries when SST Model is used \n"
         "to be equal to 2 : Turbulent intensity and ratio turbulent to laminar viscosity",
         CURRENT_FUNCTION);
+  if (Marker_Inlet_Turb != nullptr && Kind_Turb_Model == TURB_MODEL::SA && nTurb_Properties != 1)
+    SU2_MPI::Error(
+        "The use of MARKER_INLET_TURBULENT requires the number of entries when SA Model is used \n"
+        "to be equal to 1 : ratio turbulent to laminar viscosity",
+        CURRENT_FUNCTION);
 
   /*--- Checks for additional species transport. ---*/
   if (Kind_Species_Model == SPECIES_MODEL::SPECIES_TRANSPORT) {
@@ -8826,7 +8831,11 @@ const su2double* CConfig::GetInlet_TurbVal(string val_marker) const {
   for (auto iMarker = 0u; iMarker < nMarker_Inlet_Turb; iMarker++) {
     if (Marker_Inlet_Turb[iMarker] == val_marker) return Inlet_TurbVal[iMarker];
   }
-  return TurbIntensityAndViscRatioFreeStream;
+  if (Kind_Turb_Model == TURB_MODEL::SST) {
+    return TurbIntensityAndViscRatioFreeStream;
+  } else {
+    return &NuFactor_FreeStream;
+  }
 }
 
 su2double CConfig::GetOutlet_Pressure(string val_marker) const {

SU2_CFD/src/solvers/CTurbSASolver.cpp

@@ -547,7 +547,32 @@ void CTurbSASolver::BC_Inlet(CGeometry *geometry, CSolver **solver_container, CN
       su2double Inlet_Vars[MAXNVAR];
       Inlet_Vars[0] = Inlet_TurbVars[val_marker][iVertex][0];
       if (config->GetInlet_Profile_From_File()) {
-        Inlet_Vars[0] *= config->GetDensity_Ref() / config->GetViscosity_Ref();
+         Inlet_Vars[0] *= config->GetDensity_Ref() / config->GetViscosity_Ref();
+      } else {
+         /*--- Obtain fluid model for computing the nu tilde to impose at the inlet boundary. ---*/
+         CFluidModel* FluidModel = solver_container[FLOW_SOL]->GetFluidModel();
+
+         /*--- Obtain density and laminar viscosity at inlet boundary node ---*/
+
+         su2double Density_Inlet;
+         if (config->GetKind_Regime() == ENUM_REGIME::COMPRESSIBLE) {
+           Density_Inlet = V_inlet[prim_idx.Density()];
+           FluidModel->SetTDState_Prho(V_inlet[prim_idx.Pressure()], Density_Inlet);
+         } else {
+           const su2double* Scalar_Inlet = nullptr;
+           if (config->GetKind_Species_Model() != SPECIES_MODEL::NONE) {
+            Scalar_Inlet = config->GetInlet_SpeciesVal(config->GetMarker_All_TagBound(val_marker));
+           }
+           FluidModel->SetTDState_T(V_inlet[prim_idx.Temperature()], Scalar_Inlet);
+           Density_Inlet = FluidModel->GetDensity();
+         }
+         const su2double Laminar_Viscosity_Inlet = FluidModel->GetLaminarViscosity();
+         const su2double* Turb_Properties = config->GetInlet_TurbVal(config->GetMarker_All_TagBound(val_marker));
+         const su2double Nu_Factor = Turb_Properties[0];
+         Inlet_Vars[0] = Nu_Factor * Laminar_Viscosity_Inlet / Density_Inlet;
+         if (config->GetSAParsedOptions().bc) {
+           Inlet_Vars[0] *= 0.005;
+         }
       }
 
       /*--- Load the inlet turbulence variable (uniform by default). ---*/

TestCases/hybrid_regression.py

@@ -182,7 +182,7 @@ def main():
     turb_flatplate.cfg_dir   = "rans/flatplate"
     turb_flatplate.cfg_file  = "turb_SA_flatplate.cfg"
     turb_flatplate.test_iter = 20
-    turb_flatplate.test_vals = [-4.157169, -6.737133, -0.176253, 0.057446]
+    turb_flatplate.test_vals = [-4.157169, -6.736698, -0.176253, 0.057446]
     test_list.append(turb_flatplate)
 
     # ONERA M6 Wing
@@ -495,7 +495,7 @@ def main():
     ddes_flatplate.cfg_dir   = "ddes/flatplate"
     ddes_flatplate.cfg_file  = "ddes_flatplate.cfg"
     ddes_flatplate.test_iter = 10
-    ddes_flatplate.test_vals = [-2.714758, -5.883004, -0.215005, 0.023783, -618.160000]
+    ddes_flatplate.test_vals = [-2.714758, -5.882733, -0.215005, 0.023783, -618.160000]
     ddes_flatplate.unsteady  = True
     test_list.append(ddes_flatplate)
 

TestCases/parallel_regression.py

@@ -354,7 +354,7 @@ def main():
     turb_flatplate.cfg_dir   = "rans/flatplate"
     turb_flatplate.cfg_file  = "turb_SA_flatplate.cfg"
     turb_flatplate.test_iter = 20
-    turb_flatplate.test_vals = [-4.147548, -6.729213, -0.176227, 0.057731]
+    turb_flatplate.test_vals = [-4.147548, -6.728790, -0.176227, 0.057731]
     test_list.append(turb_flatplate)
 
     # Flat plate (compressible) with species inlet
@@ -953,7 +953,7 @@ def main():
     ddes_flatplate.cfg_dir   = "ddes/flatplate"
     ddes_flatplate.cfg_file  = "ddes_flatplate.cfg"
     ddes_flatplate.test_iter = 10
-    ddes_flatplate.test_vals = [-2.714758, -5.883004, -0.215005, 0.023783, -618.160000]
+    ddes_flatplate.test_vals = [-2.714758, -5.882733, -0.215005, 0.023783, -618.160000]
     ddes_flatplate.unsteady  = True
     test_list.append(ddes_flatplate)
 
@@ -1442,12 +1442,12 @@ def main():
     species2_primitiveVenturi_mixingmodel_boundedscalar.new_output = True
     test_list.append(species2_primitiveVenturi_mixingmodel_boundedscalar)
 
-    # 2 species (1 eq) primitive venturi mixing using mixing model including viscosity and thermal conductivity
+    # 2 species (1 eq) primitive venturi mixing using mixing model including viscosity, thermal conductivity and inlet markers for SA turbulence model
     species2_primitiveVenturi_mixingmodel_viscosity           = TestCase('species2_primitiveVenturi_mixingmodel_viscosity')
     species2_primitiveVenturi_mixingmodel_viscosity.cfg_dir   = "species_transport/venturi_primitive_3species"
     species2_primitiveVenturi_mixingmodel_viscosity.cfg_file  = "species2_primitiveVenturi_mixingmodel_viscosity.cfg"
     species2_primitiveVenturi_mixingmodel_viscosity.test_iter = 50
-    species2_primitiveVenturi_mixingmodel_viscosity.test_vals = [-4.725129, -4.311366, -4.610113, -5.833264, 0.552520, -4.945381, 5.000000, -1.834845, 5.000000, -5.496023, 5.000000, -1.733470, 2.277964, 0.972376, 0.608230, 0.697358]
+    species2_primitiveVenturi_mixingmodel_viscosity.test_vals = [-4.843487, -3.585775, -3.486490, -7.560246, -5.094190, 5.000000, -1.898139, 5.000000, -3.329399, 5.000000, -2.113219, 2.482224, 0.974144, 0.607217, 0.900862]
     species2_primitiveVenturi_mixingmodel_viscosity.new_output = True
     test_list.append(species2_primitiveVenturi_mixingmodel_viscosity)
 

TestCases/serial_regression.py

@@ -255,7 +255,7 @@ def main():
     turb_flatplate.cfg_dir   = "rans/flatplate"
     turb_flatplate.cfg_file  = "turb_SA_flatplate.cfg"
     turb_flatplate.test_iter = 20
-    turb_flatplate.test_vals = [-4.157169, -6.737133, -0.176253, 0.057446] #last 4 columns
+    turb_flatplate.test_vals = [-4.157169, -6.736698, -0.176253, 0.057446] #last 4 columns
     turb_flatplate.new_output  = True
     test_list.append(turb_flatplate)
 
@@ -854,7 +854,7 @@ def main():
     ddes_flatplate.cfg_dir   = "ddes/flatplate"
     ddes_flatplate.cfg_file  = "ddes_flatplate.cfg"
     ddes_flatplate.test_iter = 10
-    ddes_flatplate.test_vals = [-2.714758, -5.883004, -0.215005, 0.023783, -618.160000]
+    ddes_flatplate.test_vals = [-2.714758, -5.882733, -0.215005, 0.023783, -618.160000]
     ddes_flatplate.unsteady  = True
     ddes_flatplate.new_output = True
     test_list.append(ddes_flatplate)
@@ -886,7 +886,7 @@ def main():
     ls89_sa.cfg_dir   = "nicf/LS89"
     ls89_sa.cfg_file  = "turb_SA_PR.cfg"
     ls89_sa.test_iter = 20
-    ls89_sa.test_vals = [-5.050483, -13.389547, 0.174939, 0.430757] #last 4 columns
+    ls89_sa.test_vals = [-5.050483, -13.371788, 0.174939, 0.430757] #last 4 columns
     ls89_sa.new_output= True
     test_list.append(ls89_sa)
 

TestCases/species_transport/venturi_primitive_3species/species2_primitiveVenturi_mixingmodel_viscosity.cfg

@@ -3,7 +3,8 @@
 % SU2 configuration file                                                       %
 % Case description: Species mixing with 2 species, i.e. 1 transport equations  %
 %                   Including mixture dependent density, viscosity, thermal    %
-%                   conductivity                                               %
+%                   conductivity and different viscosity ratios at the inlets  %
+%                   for the SA turbulent model.                                %
 % Author: Cristopher Morales Ubal                                              %
 % Institution: Eindhoven University of Technology                              %
 % Date: 2022/06/27                                                             %
@@ -14,16 +15,16 @@
 % ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
 %
 SOLVER= INC_RANS
-KIND_TURB_MODEL= SST
+KIND_TURB_MODEL= SA
 %
 % ---------------- INCOMPRESSIBLE FLOW CONDITION DEFINITION -------------------%
 %
 INC_DENSITY_MODEL= VARIABLE
 INC_DENSITY_INIT= 1.1766
 %
-INC_VELOCITY_INIT= ( 1.00, 0.0, 0.0 )
+INC_VELOCITY_INIT= ( 5.00, 0.0, 0.0 )
 %
-INC_ENERGY_EQUATION= YES
+INC_ENERGY_EQUATION= NO
 INC_TEMPERATURE_INIT= 300.0
 %
 INC_NONDIM= DIMENSIONAL
@@ -62,11 +63,15 @@ MARKER_SYM= ( axis )
 SPECIFIED_INLET_PROFILE= NO
 INLET_FILENAME= inlet_venturi.dat
 INC_INLET_TYPE=  VELOCITY_INLET VELOCITY_INLET
-MARKER_INLET= ( gas_inlet,       400, 1.0, 1.0,  0.0, 0.0,\
-                air_axial_inlet, 300, 1.0, 0.0, -1.0, 0.0 )
+MARKER_INLET= ( gas_inlet,       300, 5.0, 1.0,  0.0, 0.0,\
+                air_axial_inlet, 300, 3.0, 0.0, -1.0, 0.0 )
 SPECIES_USE_STRONG_BC= NO
 MARKER_INLET_SPECIES= (gas_inlet, 1.0, \          
-                       air_axial_inlet, 0.6)           
+                       air_axial_inlet, 0.6)
+%
+%
+MARKER_INLET_TURBULENT= (gas_inlet, 5.0, \          
+                       air_axial_inlet, 3.0)           
 %
 INC_OUTLET_TYPE= PRESSURE_OUTLET
 MARKER_OUTLET= ( outlet, 0.0 )
@@ -128,7 +133,7 @@ CONV_STARTITER= 10
 %
 MESH_FILENAME= primitiveVenturi.su2
 SCREEN_OUTPUT= INNER_ITER WALL_TIME \
-               RMS_PRESSURE RMS_VELOCITY-X RMS_VELOCITY-Y RMS_TKE RMS_DISSIPATION RMS_SPECIES_0 RMS_SPECIES_1 \
+               RMS_RES \
                LINSOL_ITER LINSOL_RESIDUAL \
                LINSOL_ITER_TURB LINSOL_RESIDUAL_TURB \
                LINSOL_ITER_SPECIES LINSOL_RESIDUAL_SPECIES \

config_template.cfg

@@ -987,7 +987,8 @@ SPATIAL_FOURIER= NO
 CATALYTIC_WALL= ( NONE )
 %
 % Inlet Turbulent boundary marker(s) with the following format:
-% (inlet_marker1, TurbIntensity1, RatioTurbLamViscosity1, inlet_marker2, TurbIntensity2, RatioTurbLamViscosity2, ...)
+% SA Model: (inlet_marker1, NuFactor1, inlet_marker2, NuFactor2, ...)
+% SST Model: (inlet_marker1, TurbIntensity1, RatioTurbLamViscosity1, inlet_marker2, TurbIntensity2, RatioTurbLamViscosity2, ...)
 MARKER_INLET_TURBULENT= (inlet1, 0.05, 15, inlet2, 0.02, ...)
 
 % ------------------------ WALL ROUGHNESS DEFINITION --------------------------%