Cleaned regression tests for rough flat plate and moved to parallel regression

Author: marcosch27

SU2_CFD/src/solvers/CTurbSSTSolver.cpp

@@ -491,7 +491,6 @@ void CTurbSSTSolver::BC_HeatFlux_Wall(CGeometry *geometry, CSolver **solver_cont
         nodes->SetSolution_Old(iPoint,solution);
         nodes->SetSolution(iPoint,solution);
         LinSysRes.SetBlock_Zero(iPoint);
-        
       } else { // smooth wall
         /*--- Set wall values ---*/
         su2double density = solver_container[FLOW_SOL]->GetNodes()->GetDensity(iPoint);

TestCases/parallel_regression.py

@@ -408,6 +408,22 @@ def main():
     turb_flatplate_CC_Sarkar.test_vals = [-1.195053, 2.089306, 1.529063, 5.164703, -3.700917, 8.162921]
     test_list.append(turb_flatplate_CC_Sarkar)
 
+    # FLAT PLATE, ROUGHNESS BC KNOPP SST
+    turb_flatplate_sst_roughBCKnopp           = TestCase('turb_sst_flatplate_roughBCKnopp')
+    turb_flatplate_sst_roughBCKnopp.cfg_dir   = "rans/flatplate/roughness/bc_knopp"
+    turb_flatplate_sst_roughBCKnopp.cfg_file  = "turb_SST_flatplate_roughBCKnopp.cfg"
+    turb_flatplate_sst_roughBCKnopp.test_iter = 10
+    turb_flatplate_sst_roughBCKnopp.test_vals = [10.000000, 0.053020, -3.454853, -0.684543, -0.886080, 2.140376, 1.043068, 4.808919, -0.203494, 0.053645]
+    test_list.append(turb_flatplate_sst_roughBCKnopp)
+
+    # FLAT PLATE, ROUGHNESS BC AUPOIX SST
+    turb_flatplate_sst_roughBCAupoix           = TestCase('turb_sst_flatplate_roughBCAupoix')
+    turb_flatplate_sst_roughBCAupoix.cfg_dir   = "rans/flatplate/roughness/bc_aupoix"
+    turb_flatplate_sst_roughBCAupoix.cfg_file  = "turb_SST_flatplate_roughBCAupoix.cfg"
+    turb_flatplate_sst_roughBCAupoix.test_iter = 10
+    turb_flatplate_sst_roughBCAupoix.test_vals = [10.000000, 0.053252, -3.575414, -0.761810, -0.998912, 2.003238, 0.907276, 4.807309, -0.197354, 0.051349]
+    test_list.append(turb_flatplate_sst_roughBCAupoix)
+
     # ONERA M6 Wing
     turb_oneram6           = TestCase('turb_oneram6')
     turb_oneram6.cfg_dir   = "rans/oneram6"

TestCases/rans/flatplate/roughness/bc_aupoix/turb_SST_flatplate_roughBCAupoix.cfg

@@ -1,248 +1,109 @@
-%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-%                                                                              %
-% SU2 configuration file                                                       %
-% Case description: Turbulent flow over flat plate with zero pressure gradient %
-% Author: Thomas D. Economon                                                   %
-% Institution: Stanford University                                             %
-% Date: 2011.11.10                                                             %
-% File Version 5.0.0 "Raven"                                                %
-%                                                                              %
-%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+%                                                                                    %
+% SU2 configuration file                                                             %
+% Case description: Turbulent flow over rough flat plate with zero pressure gradient %
+% Author: Thomas D. Economon                                                         %
+% Institution: Stanford University                                                   %
+% Date: 2011.11.10                                                                   %
+% File Version 8.3.0 "Harrier"                                                       %
+%                                                                                    %
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 
 % ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
 %
-% Physical governing equations (EULER, NAVIER_STOKES,
-%                               WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY,
-%                               POISSON_EQUATION)
 SOLVER= RANS
-%
-% If Navier-Stokes, kind of turbulent model (NONE, SA, SA_NEG, SST)
 KIND_TURB_MODEL= SST
 WALL_ROUGHNESS = (wall, 400e-6)
 KIND_ROUGHSST_MODEL = LIMITER_AUPOIX
-%
-% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
 MATH_PROBLEM= DIRECT
-%
-% Restart solution (NO, YES)
 RESTART_SOL= NO
 READ_BINARY_RESTART= YES
 
 % ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------%
-%
-% Mach number (non-dimensional, based on the free-stream values)
 MACH_NUMBER= 0.2
-%
-% Angle of attack (degrees)
 AOA= 0.0
-%
-% Side-slip angle (degrees)
 SIDESLIP_ANGLE= 0.0
-%
-% Free-stream temperature (288.15 K by default)
 FREESTREAM_TEMPERATURE= 300.0
-%
-% Reynolds number (non-dimensional, based on the free-stream values)
 REYNOLDS_NUMBER= 5000000.0
-%
-% Reynolds length (in meters)
 REYNOLDS_LENGTH= 1.0
 
 % ---------------------- 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= 1.0
-%
-% Reference area for force coefficients (0 implies automatic calculation)
 REF_AREA= 2.0
 
 % -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
 %
-% Navier-Stokes wall boundary marker(s) (NONE = no marker)
 MARKER_HEATFLUX= ( wall, 0.0 )
-%
-% Inlet boundary marker(s) (NONE = no marker) 
-% Format: ( inlet marker, total temperature, total pressure, flow_direction_x, 
-%           flow_direction_y, flow_direction_z, ... )
 MARKER_INLET= ( inlet, 302.4, 118309.784, 1.0, 0.0, 0.0 )
-%
-% Outlet boundary marker(s) (NONE = no marker)
-% Format: ( outlet marker, back pressure, ... )
 MARKER_OUTLET= ( outlet, 115056.0, farfield, 115056.0 )
-%
-% Symmetry boundary marker(s) (NONE = no marker)
 MARKER_SYM= ( symmetry )
-%
-% Marker(s) of the surface to be plotted or designed
 MARKER_PLOTTING= ( wall )
-%
-% Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated
 MARKER_MONITORING= ( wall )
 
 % ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
 %
-% Numerical method for spatial gradients (GREEN_GAUSS, LEAST_SQUARES, 
-%                                         WEIGHTED_LEAST_SQUARES)
 NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
-%
-% Courant-Friedrichs-Lewy condition of the finest grid
 CFL_NUMBER= 100.0
-%
-% Adaptive CFL number (NO, YES)
 CFL_ADAPT= YES
-%
-% Parameters of the adaptive CFL number (factor down, factor up, CFL min value,
-%                                        CFL max value )
 CFL_ADAPT_PARAM= ( 0.1, 2.0, 100.0, 1e5 )
-%
-% Runge-Kutta alpha coefficients
 RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
-%
-% Number of total iterations
 ITER= 99999
 
 % ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
 %
-% Coefficient for the limiter
 VENKAT_LIMITER_COEFF= 0.1
-%
-% Coefficient for the sharp edges limiter
 ADJ_SHARP_LIMITER_COEFF= 3.0
-%
-% Reference coefficient (sensitivity) for detecting sharp edges.
 REF_SHARP_EDGES= 3.0
-%
-% Remove sharp edges from the sensitivity evaluation (NO, YES)
 SENS_REMOVE_SHARP= NO
 
 % -------------------------- MULTIGRID PARAMETERS -----------------------------%
 %
-% Multi-Grid Levels (0 = no multi-grid)
 MGLEVEL= 0
-%
-% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE)
-MGCYCLE= V_CYCLE
-%
-% Multi-grid pre-smoothing level
-MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
-%
-% Multi-grid post-smoothing level
-MG_POST_SMOOTH= ( 2, 2, 2, 2)
-%
-% Jacobi implicit smoothing of the correction
-MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )
-%
-% Damping factor for the residual restriction
-MG_DAMP_RESTRICTION= 0.8
-%
-% Damping factor for the correction prolongation
-MG_DAMP_PROLONGATION= 0.8
-
 % -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
 %
-% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
-%                              TURKEL_PREC, MSW)
 CONV_NUM_METHOD_FLOW= ROE
 %
-% Monotonic Upwind Scheme for Conservation Laws (TVD) in the flow equations.
-%           Required for 2nd order upwind schemes (NO, YES)
 MUSCL_FLOW= YES
-%
-% Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG,
-%                BARTH_JESPERSEN, VAN_ALBADA_EDGE)
 SLOPE_LIMITER_FLOW= NONE
-%
-% 2nd and 4th order artificial dissipation coefficients
 JST_SENSOR_COEFF= ( 0.5, 0.02 )
-%
-% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
 TIME_DISCRE_FLOW= EULER_IMPLICIT
 
 % -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
 %
-% Convective numerical method (SCALAR_UPWIND)
+
 CONV_NUM_METHOD_TURB= SCALAR_UPWIND
-%
-% Monotonic Upwind Scheme for Conservation Laws (TVD) in the turbulence equations.
-%           Required for 2nd order upwind schemes (NO, YES)
 MUSCL_TURB= NO
-%
-% Slope limiter (VENKATAKRISHNAN, MINMOD)
 SLOPE_LIMITER_TURB= VENKATAKRISHNAN
-%
-% Time discretization (EULER_IMPLICIT)
 TIME_DISCRE_TURB= EULER_IMPLICIT
 
 % --------------------------- CONVERGENCE PARAMETERS --------------------------%
 %
-% Convergence criteria (CAUCHY, RESIDUAL)
 CONV_FIELD= RMS_DENSITY
-%
-% Min value of the residual (log10 of the residual)
 CONV_RESIDUAL_MINVAL= -14
-%
-% Start convergence criteria at iteration number
 CONV_STARTITER= 10
-%
-% Number of elements to apply the criteria
 CONV_CAUCHY_ELEMS= 100
-%
-% Epsilon to control the series convergence
 CONV_CAUCHY_EPS= 1E-6
 %
 
 % ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
 %
-% Mesh input file
 MESH_FILENAME= mesh_flatplate_turb_137x97.su2
-%
-% Mesh input file format (SU2, CGNS, NETCDF_ASCII)
 MESH_FORMAT= SU2
-%
-% Mesh output file
 MESH_OUT_FILENAME= mesh_out.su2
-%
-% Restart flow input file
 SOLUTION_FILENAME= solution_flow.dat
-%
-% Restart adjoint input file
 SOLUTION_ADJ_FILENAME= solution_adj.dat
-%
-% Output file format (PARAVIEW, TECPLOT, SLT)
 TABULAR_FORMAT= CSV
-%
-% Output file convergence history (w/o extension) 
 CONV_FILENAME= history
-%
-% Output file restart flow
 RESTART_FILENAME= restart_flow.dat
-%
-% Output file restart adjoint
 RESTART_ADJ_FILENAME= restart_adj.dat
-%
-% Output file flow (w/o extension) variables
 VOLUME_FILENAME= flow
-%
-% Output file adjoint (w/o extension) variables
 VOLUME_ADJ_FILENAME= adjoint
-%
-% Output objective function gradient (using continuous adjoint)
 GRAD_OBJFUNC_FILENAME= of_grad.dat
-%
-% Output file surface flow coefficient (w/o extension)
 SURFACE_FILENAME= surface_flow
-%
-% Output file surface adjoint coefficient (w/o extension)
 SURFACE_ADJ_FILENAME= surface_adjoint
-%
-% Writing solution file frequency
 OUTPUT_WRT_FREQ= 1000
-%
-% 
-% Screen output
 SCREEN_OUTPUT= (INNER_ITER, WALL_TIME, RMS_RES, LIFT, DRAG)