XFOIL
https://web.mit.edu/drela/Public/web/xfoil/
コマインドラインツール
レポジトリ
GitHub - nolankucd/Xfoil-for-Mac: This is a fork of the venerable Xfoil with tweaks to allow installation on MacOS 11.
インストール
gfortranの設定が一部必要
xcode - GFortran error: ld: library not found for -lSystem when trying to compile - Stack Overflow
シェルで以下を実行
export SDKROOT=$(xcrun --sdk macosx --show-sdk-path) export LIBRARY_PATH="$LIBRARY_PATH:$SDKROOT/usr/lib"
あとはビルド手順に従う
実行
$ cd Xfoil-for-Mac/runs
$ ../bin/xfoil
===================================================
XFOIL Version 6.99
Copyright (C) 2000 Mark Drela, Harold Youngren
This software comes with ABSOLUTELY NO WARRANTY,
subject to the GNU General Public License.
Caveat computor
===================================================
File xfoil.def not found
QUIT Exit program
.OPER Direct operating point(s)
.MDES Complex mapping design routine
.QDES Surface speed design routine
.GDES Geometry design routine
SAVE f Write airfoil to labeled coordinate file
PSAV f Write airfoil to plain coordinate file
ISAV f Write airfoil to ISES coordinate file
MSAV f Write airfoil to MSES coordinate file
REVE Reverse written-airfoil node ordering
DELI i Change written-airfoil file delimiters
LOAD f Read buffer airfoil from coordinate file
NACA i Set NACA 4,5-digit airfoil and buffer airfoil
INTE Set buffer airfoil by interpolating two airfoils
NORM Buffer airfoil normalization toggle
HALF Halve the number of points in buffer airfoil
XYCM rr Change CM reference location, currently 0.25000 0.00000
BEND Display structural properties of current airfoil
PCOP Set current-airfoil panel nodes directly from buffer airfoil points
PANE Set current-airfoil panel nodes ( 160 ) based on curvature
.PPAR Show/change paneling
.PLOP Plotting options
WDEF f Write current-settings file
RDEF f Reread current-settings file
NAME s Specify new airfoil name
NINC Increment name version number
Z Zoom | (available in all menus)
U Unzoom |
XFOIL c> naca 0012
Max thickness = 0.120032 at x = 0.297
Max camber = -0.000000 at x = 0.015
Buffer airfoil set using 245 points
Blunt trailing edge. Gap = 0.00252
Paneling parameters used...
Number of panel nodes 160
Panel bunching parameter 1.000
TE/LE panel density ratio 0.150
Refined-area/LE panel density ratio 0.200
Top side refined area x/c limits 1.000 1.000
Bottom side refined area x/c limits 1.000 1.000
XFOIL c> oper
.OPERi c> alfa N
Enter angle of attack (deg) r> 5
Calculating unit vorticity distributions ...
XFLR5
https://www.xflr5.com/xflr5.htm
http://www.ina111.org/archives/10
人力飛行機の翼型の選び方 - ina111's blog
PANAIR
https://www.pdas.com/panair.html
Fortranのコンパイル時にフラグが必要
fortran - Error: Rank mismatch in argument (rank-1 and scalar) - Stack Overflow
$ gfortran -fallow-argument-mismatch panair.f90 -o panair
Aircraft Intuitive Design (AID)
https://www.mathworks.com/matlabcentral/fileexchange/66770-aircraft-intuitive-design-aid
