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Merge pull request #2124 from Zcaic/add-cst
Fix CST parameterization method
2 parents cac9492 + b0c5193 commit 26656da

6 files changed

Lines changed: 162 additions & 1 deletion

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‎AUTHORS.md‎

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@@ -137,6 +137,7 @@ VivaanKhatri
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Wally Maier
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Y. Chandukrishna
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Zan Xu
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Zcaic
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aaronyicongfu
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aeroamit
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anilvar

‎Common/src/grid_movement/CSurfaceMovement.cpp‎

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@@ -556,7 +556,8 @@ vector<vector<su2double> > CSurfaceMovement::SetSurface_Deformation(CGeometry* g
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else if ((config->GetDesign_Variable(0) == ROTATION) || (config->GetDesign_Variable(0) == TRANSLATION) ||
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(config->GetDesign_Variable(0) == SCALE) || (config->GetDesign_Variable(0) == HICKS_HENNE) ||
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(config->GetDesign_Variable(0) == SURFACE_BUMP) || (config->GetDesign_Variable(0) == ANGLE_OF_ATTACK)) {
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(config->GetDesign_Variable(0) == SURFACE_BUMP) || (config->GetDesign_Variable(0) == ANGLE_OF_ATTACK) ||
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(config->GetDesign_Variable(0) == CST)) {
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/*--- Apply rotation, displacement and stretching design variables (this
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should be done before the bump function design variables) ---*/
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@@ -586,6 +587,14 @@ vector<vector<su2double> > CSurfaceMovement::SetSurface_Deformation(CGeometry* g
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/*--- Apply the design variables to the control point position ---*/
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for (iDV = 0; iDV < config->GetnDV(); iDV++) {
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if (config ->GetDesign_Variable(iDV) == CST){
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SetCST(geometry,config,iDV,false);
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}
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}
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/*--- Apply the design variables to the control point position ---*/
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for (iDV = 0; iDV < config->GetnDV(); iDV++) {
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switch (config->GetDesign_Variable(iDV)) {
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case SURFACE_BUMP:

‎TestCases/deformation/cst/Mesh Deformation Comparison.png‎

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‎TestCases/deformation/cst/Readme.md‎

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run ```SU2_DEF naca0012.cfg``` or ```mpiexec -n 4 SU2_DEF naca0012.cfg``` <br>
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the **CST** deformation result as below: <br>
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![cst result](Mesh%20Deformation%20Comparison.png "mesh")

‎TestCases/deformation/cst/naca0012.cfg‎

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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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%
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% Euler wall boundary marker(s) (NONE = no marker)
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% Implementation identical to MARKER_SYM.
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MARKER_EULER= ( airfoil )
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% Far-field boundary marker(s) (NONE = no marker)
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MARKER_FAR= ( farfield )
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% ----------------------- GEOMETRY EVALUATION PARAMETERS ----------------------%
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%
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% Marker(s) of the surface where geometrical based function will be evaluated
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GEO_MARKER= ( airfoil )
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%
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% Description of the geometry to be analyzed (AIRFOIL, WING)
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GEO_DESCRIPTION= AIRFOIL
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%
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% Coordinate of the stations to be analyzed
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% GEO_LOCATION_STATIONS= (0.0, 0.5, 1.0)
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%
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% Geometrical bounds (Y coordinate) for the wing geometry analysis or
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% fuselage evaluation (X coordinate)
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% GEO_BOUNDS= (1.5, 3.5)
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%
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% Plot loads and Cp distributions on each airfoil section
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GEO_PLOT_STATIONS= NO
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%
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% Number of section cuts to make when calculating wing geometry
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GEO_NUMBER_STATIONS= 25
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%
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% Geometrical evaluation mode (FUNCTION, GRADIENT)
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GEO_MODE= FUNCTION
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% ----------------------- DESIGN VARIABLE PARAMETERS --------------------------%
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%
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% Kind of deformation (NO_DEFORMATION, SCALE_GRID, TRANSLATE_GRID, ROTATE_GRID,
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% FFD_SETTING, FFD_NACELLE,
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% FFD_CONTROL_POINT, FFD_CAMBER, FFD_THICKNESS, FFD_TWIST
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% FFD_CONTROL_POINT_2D, FFD_CAMBER_2D, FFD_THICKNESS_2D,
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% HICKS_HENNE, SURFACE_BUMP, SURFACE_FILE)
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DV_KIND= CST,CST
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%
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% Marker of the surface in which we are going apply the shape deformation
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DV_MARKER= ( airfoil )
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%
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% Parameters of the shape deformation
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% - NO_DEFORMATION ( 1.0 )
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% - TRANSLATE_GRID ( x_Disp, y_Disp, z_Disp ), as a unit vector
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% - ROTATE_GRID ( x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) axis, DV_VALUE in deg.
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% - SCALE_GRID ( 1.0 )
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% - ANGLE_OF_ATTACK ( 1.0 )
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% - FFD_SETTING ( 1.0 )
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% - FFD_CONTROL_POINT ( FFD_BoxTag, i_Ind, j_Ind, k_Ind, x_Disp, y_Disp, z_Disp )
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% - FFD_NACELLE ( FFD_BoxTag, rho_Ind, theta_Ind, phi_Ind, rho_Disp, phi_Disp )
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% - FFD_GULL ( FFD_BoxTag, j_Ind )
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% - FFD_ANGLE_OF_ATTACK ( FFD_BoxTag, 1.0 )
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% - FFD_CAMBER ( FFD_BoxTag, i_Ind, j_Ind )
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% - FFD_THICKNESS ( FFD_BoxTag, i_Ind, j_Ind )
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% - FFD_TWIST ( FFD_BoxTag, j_Ind, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
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% - FFD_CONTROL_POINT_2D ( FFD_BoxTag, i_Ind, j_Ind, x_Disp, y_Disp )
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% - FFD_CAMBER_2D ( FFD_BoxTag, i_Ind )
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% - FFD_THICKNESS_2D ( FFD_BoxTag, i_Ind )
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% - HICKS_HENNE ( Lower Surface (0)/Upper Surface (1)/Only one Surface (2), x_Loc )
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% - SURFACE_BUMP ( x_Start, x_End, x_Loc )
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DV_PARAM= (0, 5, 7);(1, 5, 10)
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%
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% Value of the shape deformation
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DV_VALUE= -0.5,0.5
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% ------------------------- INPUT/OUTPUT FILE INFORMATION --------------------------%
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%
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DEFORM_CONSOLE_OUTPUT= YES
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%
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% Mesh input file
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MESH_FILENAME= ../naca0012/mesh_NACA0012_inv.su2
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%
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% Mesh input file format (SU2, CGNS)
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MESH_FORMAT= SU2
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%
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% Mesh output file
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MESH_OUT_FILENAME= mesh_out.su2
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%
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% Restart flow input file
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SOLUTION_FILENAME= solution_flow.dat
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%
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% Restart adjoint input file
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SOLUTION_ADJ_FILENAME= solution_adj.dat
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%
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% Output tabular file format (TECPLOT, CSV)
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TABULAR_FORMAT= CSV
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%
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% Files to output
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% Possible formats : (TECPLOT_ASCII, TECPLOT, SURFACE_TECPLOT_ASCII,
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% SURFACE_TECPLOT, CSV, SURFACE_CSV, PARAVIEW_ASCII, PARAVIEW_LEGACY, SURFACE_PARAVIEW_ASCII,
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% SURFACE_PARAVIEW_LEGACY, PARAVIEW, SURFACE_PARAVIEW, RESTART_ASCII, RESTART, CGNS, SURFACE_CGNS, STL_ASCII, STL_BINARY)
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% default : (RESTART, PARAVIEW, SURFACE_PARAVIEW)
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OUTPUT_FILES= (RESTART, PARAVIEW_MULTIBLOCK)
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%
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% Output file convergence history (w/o extension)
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CONV_FILENAME= history
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%
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% Output file with the forces breakdown
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BREAKDOWN_FILENAME= forces_breakdown.dat
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%
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% Output file restart flow
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RESTART_FILENAME= restart_flow.dat
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%
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% Output file restart adjoint
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RESTART_ADJ_FILENAME= restart_adj.dat
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%
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% Output file flow (w/o extension) variables
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VOLUME_FILENAME= flow
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%
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% Output file adjoint (w/o extension) variables
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VOLUME_ADJ_FILENAME= adjoint
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%
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% Output Objective function
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VALUE_OBJFUNC_FILENAME= of_eval.dat
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%
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% Output objective function gradient (using continuous adjoint)
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GRAD_OBJFUNC_FILENAME= of_grad.dat
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%
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% Output file surface flow coefficient (w/o extension)
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SURFACE_FILENAME= surface_flow
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%
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% Output file surface adjoint coefficient (w/o extension)
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SURFACE_ADJ_FILENAME= surface_adjoint
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%
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% Read binary restart files (YES, NO)
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READ_BINARY_RESTART= YES
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%
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% Reorient elements based on potential negative volumes (YES/NO)
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REORIENT_ELEMENTS= YES
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%

‎TestCases/parallel_regression.py‎

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@@ -1771,6 +1771,19 @@ def main():
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pass_list.append(sphere_ffd_def_bspline.run_def())
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test_list.append(sphere_ffd_def_bspline)
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# Inviscid NACA0012 (triangles)
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naca0012_cst = TestCase('naca0012_cst')
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naca0012_cst.cfg_dir = "deformation/cst"
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naca0012_cst.cfg_file = "naca0012.cfg"
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naca0012_cst.test_iter = 10
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naca0012_cst.test_vals = [0.000385514] #residual
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naca0012_cst.command = TestCase.Command("mpirun -n 2", "SU2_DEF")
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naca0012_cst.timeout = 1600
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naca0012_cst.tol = 1e-8
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pass_list.append(naca0012_cst.run_def())
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test_list.append(naca0012_cst)
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# 2D FD streamwise periodic cht, avg temp obj func
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fd_sp_pinArray_cht_2d_dp_hf = TestCase('fd_sp_pinArray_cht_2d_dp_hf')
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fd_sp_pinArray_cht_2d_dp_hf.cfg_dir = "incomp_navierstokes/streamwise_periodic/chtPinArray_2d"

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