su2code · pcarruscag · Jul 21, 2023 · Jul 2, 2023 · Jul 11, 2023 · Jul 20, 2023
diff --git a/compressible_flow/QuickStart/Makefile b/compressible_flow/QuickStart/Makefile
@@ -0,0 +1,73 @@
+## \file Makefile
+#  \brief Makefile for the QuickStart tutorial
+#  \author F. Poli
+#  \version 7.5.1 "Blackbird"
+#
+# SU2 Project Website: https://su2code.github.io
+#
+# The SU2 Project is maintained by the SU2 Foundation
+# (http://su2foundation.org)
+#
+# Copyright 2023, SU2 Contributors (cf. AUTHORS.md)
+#
+# SU2 is free software; you can redistribute it and/or
+# modify it under the terms of the GNU Lesser General Public
+# License as published by the Free Software Foundation; either
+# version 2.1 of the License, or (at your option) any later version.
+#
+# SU2 is distributed in the hope that it will be useful,
+# but WITHOUT ANY WARRANTY; without even the implied warranty of
+# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
+# Lesser General Public License for more details.
+#
+# You should have received a copy of the GNU Lesser General Public
+# License along with SU2. If not, see <http://www.gnu.org/licenses/>.
+
+TIME=/usr/bin/time
+
+all: restart_flow.dat NACA0012_coef_pres.pdf NACA0012_pressure_field.png \
+     adj/restart_adj_cd.dat dadj/restart_adj_cd.dat \
+     NACA0012_surf_sens.pdf \
+     NACA0012_coef_pres.png NACA0012_surf_sens.png
+
+restart_flow.dat: inv_NACA0012.cfg mesh_NACA0012_inv.su2
+	$(TIME) -o su2_cfd_time.out SU2_CFD $< | tee su2_cfd.log 
+
+NACA0012_coef_pres.pdf: NACA0012_coef_pres.tex restart_flow.dat surface_flow.csv
+	texfot -q lualatex $<
+
+NACA0012_pressure_field.png: make_field_shots.py restart_flow.dat flow.vtu
+	python3 make_field_shots.py
+
+adj/restart_adj_cd.dat: adj/inv_adj_NACA0012.cfg mesh_NACA0012_inv.su2 \
+                        restart_flow.dat
+	cd adj \
+	&& ln -sf ../mesh_NACA0012_inv.su2 ./mesh_NACA0012_inv.su2 \
+	&& ln -sf ../restart_flow.dat ./solution_flow.dat \
+	&& $(TIME) -o su2_cfd_adj_time.out \
+	           SU2_CFD inv_adj_NACA0012.cfg | tee su2_cfd_adj.log
+
+dadj/restart_adj_cd.dat: dadj/inv_dadj_NACA0012.cfg mesh_NACA0012_inv.su2 \
+                         restart_flow.dat
+	cd dadj \
+	&& ln -sf ../mesh_NACA0012_inv.su2 ./mesh_NACA0012_inv.su2 \
+	&& ln -sf ../restart_flow.dat ./solution_flow.dat \
+	&& $(TIME) -o su2_cfd_ad_dadj_time.out \
+	           SU2_CFD_AD inv_dadj_NACA0012.cfg | tee su2_cfd_ad_dadj.log
+
+NACA0012_surf_sens.pdf: NACA0012_surf_sens.tex \
+                        adj/restart_adj_cd.dat dadj/restart_adj_cd.dat \
+                        adj/surface_adjoint.csv dadj/surface_adjoint.csv
+	texfot -q lualatex $<
+
+%.png: %.pdf
+	convert -density 154x154 $< $@
+
+.PHONY: clean
+clean:
+	-rm -f *.log *.aux *.out *adj/*.log *adj/*.out
+	-rm -f *adj/solution_flow.dat *adj/mesh_NACA0012_inv.su2
+
+.PHONY: distclean
+distclean: clean
+	-rm -f *.vtu *.csv *.dat *adj/*.csv *adj/*.dat *.png *.pdf
diff --git a/compressible_flow/QuickStart/NACA0012_coef_pres.tex b/compressible_flow/QuickStart/NACA0012_coef_pres.tex
@@ -0,0 +1,72 @@
+\documentclass[tikz,margin=1pt]{standalone}
+
+%% \file NACA0012_coef_pres.tex
+%  \brief LaTeX code for the C_p plot in the QuickStart tutorial
+%  \author F. Poli
+%  \version 7.5.1 "Blackbird"
+%
+% SU2 Project Website: https://su2code.github.io
+%
+% The SU2 Project is maintained by the SU2 Foundation
+% (http://su2foundation.org)
+%
+% Copyright 2023, SU2 Contributors (cf. AUTHORS.md)
+%
+% SU2 is free software; you can redistribute it and/or
+% modify it under the terms of the GNU Lesser General Public
+% License as published by the Free Software Foundation; either
+% version 2.1 of the License, or (at your option) any later version.
+%
+% SU2 is distributed in the hope that it will be useful,
+% but WITHOUT ANY WARRANTY; without even the implied warranty of
+% MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
+% Lesser General Public License for more details.
+%
+% You should have received a copy of the GNU Lesser General Public
+% License along with SU2. If not, see <http://www.gnu.org/licenses/>.
+
+\usepackage{pgfplots}
+\pgfplotsset{compat=1.17,trig format plots=rad,tick scale binop=\times,
+ /pgf/number format/sci generic={mantissa sep=\times,exponent={10^{#1}}},
+ /pgf/number format/1000 sep={\,}}
+%\usepgfplotslibrary{groupplots}
+%\usepgfplotslibrary{patchplots}
+\usepackage{pgfplotstable}
+\begin{document}
+  \begin{tikzpicture}
+    \pagecolor{white}
+    \begin{axis}
+    [
+      title={Coefficient of pressure for the NACA 0012 airfoil},
+      width=108mm,
+      height=88mm,
+      xlabel={$x/c$},
+      ylabel={$C_p$},
+      enlarge x limits=false,
+      %enlarge y limits=true,
+      ymin=-1.5,ymax=1.5,
+      y dir=reverse,
+      %ymajorgrids=true,
+      legend cell align=left,
+      legend pos=south east,
+      table/col sep=comma,
+    ]
+      \addplot%+
+      [
+        blue!50!black,
+        thick,
+        mark=*,
+        mark size=0.7,
+      ]
+      table
+      [
+        x="x",
+        y="Pressure_Coefficient",
+      ]
+      {surface_flow.csv};
+      \addlegendentry{SU2}
+    \end{axis}
+  \end{tikzpicture}
+\end{document}
+
+
diff --git a/compressible_flow/QuickStart/NACA0012_surf_sens.tex b/compressible_flow/QuickStart/NACA0012_surf_sens.tex
@@ -0,0 +1,85 @@
+\documentclass[tikz,margin=1pt]{standalone}
+
+%% \file NACA0012_surf_sens.tex
+%  \brief LaTeX code for the sensitivity plot in the QuickStart tutorial
+%  \author F. Poli
+%  \version 7.5.1 "Blackbird"
+%
+% SU2 Project Website: https://su2code.github.io
+%
+% The SU2 Project is maintained by the SU2 Foundation
+% (http://su2foundation.org)
+%
+% Copyright 2023, SU2 Contributors (cf. AUTHORS.md)
+%
+% SU2 is free software; you can redistribute it and/or
+% modify it under the terms of the GNU Lesser General Public
+% License as published by the Free Software Foundation; either
+% version 2.1 of the License, or (at your option) any later version.
+%
+% SU2 is distributed in the hope that it will be useful,
+% but WITHOUT ANY WARRANTY; without even the implied warranty of
+% MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
+% Lesser General Public License for more details.
+%
+% You should have received a copy of the GNU Lesser General Public
+% License along with SU2. If not, see <http://www.gnu.org/licenses/>.
+
+\usepackage{pgfplots}
+\pgfplotsset{compat=1.17,trig format plots=rad,tick scale binop=\times,
+ /pgf/number format/sci generic={mantissa sep=\times,exponent={10^{#1}}},
+ /pgf/number format/1000 sep={\,}}
+%\usepgfplotslibrary{groupplots}
+%\usepgfplotslibrary{patchplots}
+\usepackage{pgfplotstable}
+\begin{document}
+  \begin{tikzpicture}
+    \pagecolor{white}
+    \begin{axis}
+    [
+      title={Surface sensitivities for the NACA 0012 airfoil},
+      width=108mm,
+      height=88mm,
+      xlabel={$x/c$},
+      ylabel={surface sensitivity},
+      enlarge x limits=false,
+      %enlarge y limits=true,
+      ymin=-2,ymax=2,
+      %ymajorgrids=true,
+      legend cell align=left,
+      legend pos=south west,
+      table/col sep=comma,
+    ]
+      \addplot%+
+      [
+        blue!50!black,
+        thick,
+        mark=*,
+        mark size=0.7,
+      ]
+      table
+      [
+        x="x",
+        y="Surface_Sensitivity",
+      ]
+      {adj/surface_adjoint.csv};
+      \addlegendentry{SU2 continuous adjoint}
+      \addplot%+
+      [
+        blue!40!white,
+        thick,
+        mark=*,
+        mark size=0.7,
+      ]
+      table
+      [
+        x="x",
+        y="Surface_Sensitivity",
+      ]
+      {dadj/surface_adjoint.csv};
+      \addlegendentry{SU2 discrete adjoint}
+    \end{axis}
+  \end{tikzpicture}
+\end{document}
+
+
diff --git a/compressible_flow/QuickStart/adj/inv_adj_NACA0012.cfg b/compressible_flow/QuickStart/adj/inv_adj_NACA0012.cfg
@@ -0,0 +1,135 @@
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+%                                                                              %
+% SU2 configuration file                                                       %
+% Case description: Transonic inviscid flow around a NACA0012 airfoil          %
+% Author: Thomas D. Economon                                                   %
+% Institution: Stanford University                                             %
+% Date: 2014.06.11                                                             %
+% File Version 7.5.1 "Blackbird"                                               %
+%                                                                              %
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
+
+SOLVER= EULER
+MATH_PROBLEM= CONTINUOUS_ADJOINT
+RESTART_SOL= NO
+
+% ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------%
+
+MACH_NUMBER= 0.8
+AOA= 1.25
+FREESTREAM_PRESSURE= 101325.0
+FREESTREAM_TEMPERATURE= 273.15
+
+% -------------- COMPRESSIBLE AND INCOMPRESSIBLE FLUID CONSTANTS --------------%
+
+GAMMA_VALUE= 1.4
+GAS_CONSTANT= 287.87
+
+% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
+
+REF_ORIGIN_MOMENT_X = 0.25
+REF_ORIGIN_MOMENT_Y = 0.00
+REF_ORIGIN_MOMENT_Z = 0.00
+REF_LENGTH= 1.0
+REF_AREA= 1.0
+REF_DIMENSIONALIZATION= DIMENSIONAL
+
+% ----------------------- BOUNDARY CONDITION DEFINITION -----------------------%
+
+MARKER_EULER= ( airfoil )
+MARKER_FAR= ( farfield )
+
+% ------------------------ SURFACES IDENTIFICATION ----------------------------%
+
+MARKER_PLOTTING = ( airfoil )
+MARKER_MONITORING = ( airfoil )
+MARKER_DESIGNING = ( airfoil )
+
+% ------------- COMMON PARAMETERS TO DEFINE THE NUMERICAL METHOD --------------%
+
+NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
+OBJECTIVE_FUNCTION= DRAG
+CFL_NUMBER= 1e3
+CFL_ADAPT= NO
+CFL_ADAPT_PARAM= ( 0.1, 2.0, 10.0, 1e10 )
+ITER= 250
+
+% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
+
+LINEAR_SOLVER= FGMRES
+LINEAR_SOLVER_PREC= ILU
+LINEAR_SOLVER_ERROR= 1E-10
+LINEAR_SOLVER_ITER= 10
+
+% -------------------------- MULTIGRID PARAMETERS -----------------------------%
+
+MGLEVEL= 3
+MGCYCLE= W_CYCLE
+MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
+MG_POST_SMOOTH= ( 0, 0, 0, 0 )
+MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )
+MG_DAMP_RESTRICTION= 1.0
+MG_DAMP_PROLONGATION= 1.0
+
+% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
+
+CONV_NUM_METHOD_FLOW= JST
+JST_SENSOR_COEFF= ( 0.5, 0.02 )
+TIME_DISCRE_FLOW= EULER_IMPLICIT
+
+% ---------------- ADJOINT-FLOW NUMERICAL METHOD DEFINITION -------------------%
+
+CONV_NUM_METHOD_ADJFLOW= JST
+CFL_REDUCTION_ADJFLOW= 0.01
+TIME_DISCRE_ADJFLOW= EULER_IMPLICIT
+
+% ----------------------- DESIGN VARIABLE PARAMETERS --------------------------%
+
+DV_KIND= HICKS_HENNE
+DV_MARKER= ( airfoil )
+DV_PARAM= ( 1, 0.5 )
+DV_VALUE= 0.01
+
+% ------------------------ GRID DEFORMATION PARAMETERS ------------------------%
+
+DEFORM_LINEAR_SOLVER_ITER= 500
+DEFORM_NONLINEAR_ITER= 1
+DEFORM_LINEAR_SOLVER_ERROR= 1E-14
+DEFORM_CONSOLE_OUTPUT= YES
+DEFORM_STIFFNESS_TYPE= INVERSE_VOLUME
+
+% --------------------------- CONVERGENCE PARAMETERS --------------------------%
+
+CONV_FIELD= RMS_DENSITY
+CONV_RESIDUAL_MINVAL= -8
+CONV_STARTITER= 10
+CONV_CAUCHY_ELEMS= 100
+CONV_CAUCHY_EPS= 1E-6
+SCREEN_OUTPUT=(INNER_ITER, WALL_TIME, RMS_RES, LIFT, DRAG, CAUCHY_SENS_PRESS, CAUCHY_DRAG RMS_ADJ_DENSITY RMS_ADJ_ENERGY)
+
+% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
+
+MESH_FILENAME= mesh_NACA0012_inv.su2
+MESH_FORMAT= SU2
+MESH_OUT_FILENAME= mesh_out.su2
+SOLUTION_FILENAME= solution_flow.dat
+SOLUTION_ADJ_FILENAME= solution_adj.dat
+TABULAR_FORMAT= CSV
+CONV_FILENAME= history
+RESTART_FILENAME= restart_flow.dat
+RESTART_ADJ_FILENAME= restart_adj.dat
+VOLUME_FILENAME= flow
+VOLUME_ADJ_FILENAME= adjoint
+GRAD_OBJFUNC_FILENAME= of_grad.dat
+SURFACE_FILENAME= surface_flow
+SURFACE_ADJ_FILENAME= surface_adjoint
+OUTPUT_WRT_FREQ= 250
+OUTPUT_FILES= (RESTART, SURFACE_CSV)
+
+% --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------%
+
+OPT_OBJECTIVE= DRAG * 0.001
+OPT_CONSTRAINT= ( LIFT > 0.328188 ) * 0.001; ( MOMENT_Z > 0.034068 ) * 0.001; ( AIRFOIL_THICKNESS > 0.11 ) * 0.001
+DEFINITION_DV= ( 30, 1.0 | airfoil | 0, 0.05 ); ( 30, 1.0 | airfoil | 0, 0.10 ); ( 30, 1.0 | airfoil | 0, 0.15 ); ( 30, 1.0 | airfoil | 0, 0.20 ); ( 30, 1.0 | airfoil | 0, 0.25 ); ( 30, 1.0 | airfoil | 0, 0.30 ); ( 30, 1.0 | airfoil | 0, 0.35 ); ( 30, 1.0 | airfoil | 0, 0.40 ); ( 30, 1.0 | airfoil | 0, 0.45 ); ( 30, 1.0 | airfoil | 0, 0.50 ); ( 30, 1.0 | airfoil | 0, 0.55 ); ( 30, 1.0 | airfoil | 0, 0.60 ); ( 30, 1.0 | airfoil | 0, 0.65 ); ( 30, 1.0 | airfoil | 0, 0.70 ); ( 30, 1.0 | airfoil | 0, 0.75 ); ( 30, 1.0 | airfoil | 0, 0.80 ); ( 30, 1.0 | airfoil | 0, 0.85 ); ( 30, 1.0 | airfoil | 0, 0.90 ); ( 30, 1.0 | airfoil | 0, 0.95 ); ( 30, 1.0 | airfoil | 1, 0.05 ); ( 30, 1.0 | airfoil | 1, 0.10 ); ( 30, 1.0 | airfoil | 1, 0.15 ); ( 30, 1.0 | airfoil | 1, 0.20 ); ( 30, 1.0 | airfoil | 1, 0.25 ); ( 30, 1.0 | airfoil | 1, 0.30 ); ( 30, 1.0 | airfoil | 1, 0.35 ); ( 30, 1.0 | airfoil | 1, 0.40 ); ( 30, 1.0 | airfoil | 1, 0.45 ); ( 30, 1.0 | airfoil | 1, 0.50 ); ( 30, 1.0 | airfoil | 1, 0.55 ); ( 30, 1.0 | airfoil | 1, 0.60 ); ( 30, 1.0 | airfoil | 1, 0.65 ); ( 30, 1.0 | airfoil | 1, 0.70 ); ( 30, 1.0 | airfoil | 1, 0.75 ); ( 30, 1.0 | airfoil | 1, 0.80 ); ( 30, 1.0 | airfoil | 1, 0.85 ); ( 30, 1.0 | airfoil | 1, 0.90 ); ( 30, 1.0 | airfoil | 1, 0.95 )