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add files for QuickStart tutorial (#43)
* add files for QuickStart tutorial Auxiliary source files were also included to automate the tutorial simulations and the visualization of results (with ParaView and LaTeX PGFPlots). * drop mesh and main config from QuickStart Those files have been moved back to the SU2 code repository. * strip out comments from QuickStart config files
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‎compressible_flow/QuickStart/Makefile

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## \file Makefile
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# \brief Makefile for the QuickStart tutorial
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# \author F. Poli
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# \version 7.5.1 "Blackbird"
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#
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# SU2 Project Website: https://su2code.github.io
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#
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# The SU2 Project is maintained by the SU2 Foundation
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# (http://su2foundation.org)
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#
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# Copyright 2023, SU2 Contributors (cf. AUTHORS.md)
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#
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# SU2 is free software; you can redistribute it and/or
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# modify it under the terms of the GNU Lesser General Public
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# License as published by the Free Software Foundation; either
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# version 2.1 of the License, or (at your option) any later version.
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#
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# SU2 is distributed in the hope that it will be useful,
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# but WITHOUT ANY WARRANTY; without even the implied warranty of
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# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
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# Lesser General Public License for more details.
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#
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# You should have received a copy of the GNU Lesser General Public
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# License along with SU2. If not, see <http://www.gnu.org/licenses/>.
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TIME=/usr/bin/time
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all: restart_flow.dat NACA0012_coef_pres.pdf NACA0012_pressure_field.png \
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adj/restart_adj_cd.dat dadj/restart_adj_cd.dat \
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NACA0012_surf_sens.pdf \
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NACA0012_coef_pres.png NACA0012_surf_sens.png
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restart_flow.dat: inv_NACA0012.cfg mesh_NACA0012_inv.su2
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$(TIME) -o su2_cfd_time.out SU2_CFD $< | tee su2_cfd.log
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NACA0012_coef_pres.pdf: NACA0012_coef_pres.tex restart_flow.dat surface_flow.csv
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texfot -q lualatex $<
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NACA0012_pressure_field.png: make_field_shots.py restart_flow.dat flow.vtu
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python3 make_field_shots.py
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adj/restart_adj_cd.dat: adj/inv_adj_NACA0012.cfg mesh_NACA0012_inv.su2 \
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restart_flow.dat
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cd adj \
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&& ln -sf ../mesh_NACA0012_inv.su2 ./mesh_NACA0012_inv.su2 \
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&& ln -sf ../restart_flow.dat ./solution_flow.dat \
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&& $(TIME) -o su2_cfd_adj_time.out \
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SU2_CFD inv_adj_NACA0012.cfg | tee su2_cfd_adj.log
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dadj/restart_adj_cd.dat: dadj/inv_dadj_NACA0012.cfg mesh_NACA0012_inv.su2 \
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restart_flow.dat
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cd dadj \
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&& ln -sf ../mesh_NACA0012_inv.su2 ./mesh_NACA0012_inv.su2 \
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&& ln -sf ../restart_flow.dat ./solution_flow.dat \
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&& $(TIME) -o su2_cfd_ad_dadj_time.out \
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SU2_CFD_AD inv_dadj_NACA0012.cfg | tee su2_cfd_ad_dadj.log
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NACA0012_surf_sens.pdf: NACA0012_surf_sens.tex \
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adj/restart_adj_cd.dat dadj/restart_adj_cd.dat \
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adj/surface_adjoint.csv dadj/surface_adjoint.csv
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texfot -q lualatex $<
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%.png: %.pdf
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convert -density 154x154 $< $@
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.PHONY: clean
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clean:
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-rm -f *.log *.aux *.out *adj/*.log *adj/*.out
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-rm -f *adj/solution_flow.dat *adj/mesh_NACA0012_inv.su2
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.PHONY: distclean
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distclean: clean
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-rm -f *.vtu *.csv *.dat *adj/*.csv *adj/*.dat *.png *.pdf

‎compressible_flow/QuickStart/NACA0012_coef_pres.tex

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\documentclass[tikz,margin=1pt]{standalone}
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%% \file NACA0012_coef_pres.tex
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% \brief LaTeX code for the C_p plot in the QuickStart tutorial
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% \author F. Poli
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% \version 7.5.1 "Blackbird"
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%
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% SU2 Project Website: https://su2code.github.io
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%
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% The SU2 Project is maintained by the SU2 Foundation
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% (http://su2foundation.org)
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%
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% Copyright 2023, SU2 Contributors (cf. AUTHORS.md)
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%
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% SU2 is free software; you can redistribute it and/or
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% modify it under the terms of the GNU Lesser General Public
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% License as published by the Free Software Foundation; either
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% version 2.1 of the License, or (at your option) any later version.
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%
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% SU2 is distributed in the hope that it will be useful,
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% but WITHOUT ANY WARRANTY; without even the implied warranty of
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% MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
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% Lesser General Public License for more details.
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%
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% You should have received a copy of the GNU Lesser General Public
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% License along with SU2. If not, see <http://www.gnu.org/licenses/>.
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\usepackage{pgfplots}
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\pgfplotsset{compat=1.17,trig format plots=rad,tick scale binop=\times,
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/pgf/number format/sci generic={mantissa sep=\times,exponent={10^{#1}}},
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/pgf/number format/1000 sep={\,}}
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%\usepgfplotslibrary{groupplots}
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%\usepgfplotslibrary{patchplots}
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\usepackage{pgfplotstable}
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\begin{document}
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\begin{tikzpicture}
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\pagecolor{white}
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\begin{axis}
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[
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title={Coefficient of pressure for the NACA 0012 airfoil},
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width=108mm,
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height=88mm,
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xlabel={$x/c$},
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ylabel={$C_p$},
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enlarge x limits=false,
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%enlarge y limits=true,
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ymin=-1.5,ymax=1.5,
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y dir=reverse,
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%ymajorgrids=true,
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legend cell align=left,
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legend pos=south east,
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table/col sep=comma,
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]
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\addplot%+
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[
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blue!50!black,
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thick,
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mark=*,
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mark size=0.7,
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]
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table
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[
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x="x",
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y="Pressure_Coefficient",
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]
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{surface_flow.csv};
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\addlegendentry{SU2}
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\end{axis}
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\end{tikzpicture}
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\end{document}
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‎compressible_flow/QuickStart/NACA0012_surf_sens.tex

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\documentclass[tikz,margin=1pt]{standalone}
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%% \file NACA0012_surf_sens.tex
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% \brief LaTeX code for the sensitivity plot in the QuickStart tutorial
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% \author F. Poli
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% \version 7.5.1 "Blackbird"
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%
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% SU2 Project Website: https://su2code.github.io
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%
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% The SU2 Project is maintained by the SU2 Foundation
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% (http://su2foundation.org)
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%
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% Copyright 2023, SU2 Contributors (cf. AUTHORS.md)
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%
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% SU2 is free software; you can redistribute it and/or
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% modify it under the terms of the GNU Lesser General Public
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% License as published by the Free Software Foundation; either
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% version 2.1 of the License, or (at your option) any later version.
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%
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% SU2 is distributed in the hope that it will be useful,
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% but WITHOUT ANY WARRANTY; without even the implied warranty of
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% MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
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% Lesser General Public License for more details.
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%
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% You should have received a copy of the GNU Lesser General Public
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% License along with SU2. If not, see <http://www.gnu.org/licenses/>.
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\usepackage{pgfplots}
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\pgfplotsset{compat=1.17,trig format plots=rad,tick scale binop=\times,
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/pgf/number format/sci generic={mantissa sep=\times,exponent={10^{#1}}},
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/pgf/number format/1000 sep={\,}}
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%\usepgfplotslibrary{groupplots}
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%\usepgfplotslibrary{patchplots}
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\usepackage{pgfplotstable}
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\begin{document}
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\begin{tikzpicture}
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\pagecolor{white}
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\begin{axis}
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[
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title={Surface sensitivities for the NACA 0012 airfoil},
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width=108mm,
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height=88mm,
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xlabel={$x/c$},
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ylabel={surface sensitivity},
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enlarge x limits=false,
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%enlarge y limits=true,
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ymin=-2,ymax=2,
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%ymajorgrids=true,
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legend cell align=left,
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legend pos=south west,
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table/col sep=comma,
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]
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\addplot%+
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[
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blue!50!black,
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thick,
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mark=*,
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mark size=0.7,
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]
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table
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[
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x="x",
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y="Surface_Sensitivity",
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]
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{adj/surface_adjoint.csv};
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\addlegendentry{SU2 continuous adjoint}
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\addplot%+
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[
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blue!40!white,
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thick,
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mark=*,
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mark size=0.7,
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]
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table
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[
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x="x",
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y="Surface_Sensitivity",
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]
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{dadj/surface_adjoint.csv};
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\addlegendentry{SU2 discrete adjoint}
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\end{axis}
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\end{tikzpicture}
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\end{document}
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‎compressible_flow/QuickStart/adj/inv_adj_NACA0012.cfg

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: Transonic inviscid flow around a NACA0012 airfoil %
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% Author: Thomas D. Economon %
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% Institution: Stanford University %
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% Date: 2014.06.11 %
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% File Version 7.5.1 "Blackbird" %
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% %
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
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SOLVER= EULER
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MATH_PROBLEM= CONTINUOUS_ADJOINT
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RESTART_SOL= NO
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% ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------%
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MACH_NUMBER= 0.8
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AOA= 1.25
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FREESTREAM_PRESSURE= 101325.0
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FREESTREAM_TEMPERATURE= 273.15
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% -------------- COMPRESSIBLE AND INCOMPRESSIBLE FLUID CONSTANTS --------------%
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GAMMA_VALUE= 1.4
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GAS_CONSTANT= 287.87
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% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
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REF_ORIGIN_MOMENT_X = 0.25
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REF_ORIGIN_MOMENT_Y = 0.00
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REF_ORIGIN_MOMENT_Z = 0.00
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REF_LENGTH= 1.0
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REF_AREA= 1.0
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REF_DIMENSIONALIZATION= DIMENSIONAL
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% ----------------------- BOUNDARY CONDITION DEFINITION -----------------------%
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MARKER_EULER= ( airfoil )
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MARKER_FAR= ( farfield )
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% ------------------------ SURFACES IDENTIFICATION ----------------------------%
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MARKER_PLOTTING = ( airfoil )
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MARKER_MONITORING = ( airfoil )
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MARKER_DESIGNING = ( airfoil )
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% ------------- COMMON PARAMETERS TO DEFINE THE NUMERICAL METHOD --------------%
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NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
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OBJECTIVE_FUNCTION= DRAG
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CFL_NUMBER= 1e3
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CFL_ADAPT= NO
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CFL_ADAPT_PARAM= ( 0.1, 2.0, 10.0, 1e10 )
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ITER= 250
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% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
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LINEAR_SOLVER= FGMRES
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LINEAR_SOLVER_PREC= ILU
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LINEAR_SOLVER_ERROR= 1E-10
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LINEAR_SOLVER_ITER= 10
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% -------------------------- MULTIGRID PARAMETERS -----------------------------%
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MGLEVEL= 3
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MGCYCLE= W_CYCLE
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MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
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MG_POST_SMOOTH= ( 0, 0, 0, 0 )
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MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )
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MG_DAMP_RESTRICTION= 1.0
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MG_DAMP_PROLONGATION= 1.0
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% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
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CONV_NUM_METHOD_FLOW= JST
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JST_SENSOR_COEFF= ( 0.5, 0.02 )
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TIME_DISCRE_FLOW= EULER_IMPLICIT
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% ---------------- ADJOINT-FLOW NUMERICAL METHOD DEFINITION -------------------%
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CONV_NUM_METHOD_ADJFLOW= JST
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CFL_REDUCTION_ADJFLOW= 0.01
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TIME_DISCRE_ADJFLOW= EULER_IMPLICIT
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% ----------------------- DESIGN VARIABLE PARAMETERS --------------------------%
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DV_KIND= HICKS_HENNE
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DV_MARKER= ( airfoil )
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DV_PARAM= ( 1, 0.5 )
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DV_VALUE= 0.01
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% ------------------------ GRID DEFORMATION PARAMETERS ------------------------%
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DEFORM_LINEAR_SOLVER_ITER= 500
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DEFORM_NONLINEAR_ITER= 1
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DEFORM_LINEAR_SOLVER_ERROR= 1E-14
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DEFORM_CONSOLE_OUTPUT= YES
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DEFORM_STIFFNESS_TYPE= INVERSE_VOLUME
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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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CONV_FIELD= RMS_DENSITY
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CONV_RESIDUAL_MINVAL= -8
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CONV_STARTITER= 10
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CONV_CAUCHY_ELEMS= 100
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CONV_CAUCHY_EPS= 1E-6
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SCREEN_OUTPUT=(INNER_ITER, WALL_TIME, RMS_RES, LIFT, DRAG, CAUCHY_SENS_PRESS, CAUCHY_DRAG RMS_ADJ_DENSITY RMS_ADJ_ENERGY)
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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MESH_FILENAME= mesh_NACA0012_inv.su2
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MESH_FORMAT= SU2
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MESH_OUT_FILENAME= mesh_out.su2
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SOLUTION_FILENAME= solution_flow.dat
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SOLUTION_ADJ_FILENAME= solution_adj.dat
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TABULAR_FORMAT= CSV
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CONV_FILENAME= history
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RESTART_FILENAME= restart_flow.dat
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RESTART_ADJ_FILENAME= restart_adj.dat
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VOLUME_FILENAME= flow
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VOLUME_ADJ_FILENAME= adjoint
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GRAD_OBJFUNC_FILENAME= of_grad.dat
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SURFACE_FILENAME= surface_flow
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SURFACE_ADJ_FILENAME= surface_adjoint
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OUTPUT_WRT_FREQ= 250
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OUTPUT_FILES= (RESTART, SURFACE_CSV)
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% --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------%
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OPT_OBJECTIVE= DRAG * 0.001
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OPT_CONSTRAINT= ( LIFT > 0.328188 ) * 0.001; ( MOMENT_Z > 0.034068 ) * 0.001; ( AIRFOIL_THICKNESS > 0.11 ) * 0.001
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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 )

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