One quick question: how to increase the number of digits in the polar output values of CL, CD, and CM calculated from XFoil? XFoil only outputs 4 digits after the decimal for CL and CM, and 5 digits for CD. Thanks a lot for the video!
Hi,thank you for the video. But When I run this code, I always an error that "xfoil.exe: not found". I can use xfoil on terminal screen. There is no problem. Why I take this error? Thank you.
Hello thank you for the video, can I run it with another airfoil like NACA001X? And if the answer is yes, where can find the data file of the said airfoil?
very nice! Thank you so much, kind person
Hola José !
Muchas gracias para suyo trábajo !
Es muy conveniente !
Mano, safaste um gajo, rei, propz
Extremely useful!
Thanks a lot, very useful ! I was trying to use the xfoil python module but it is working quite weirdly
One quick question: how to increase the number of digits in the polar output values of CL, CD, and CM calculated from XFoil? XFoil only outputs 4 digits after the decimal for CL and CM, and 5 digits for CD.
Thanks a lot for the video!
nice
Hi, have you made a code that is compatible with the XFOILVG version? I can't modify your code for this version
Hi,thank you for the video. But When I run this code, I always an error that "xfoil.exe: not found". I can use xfoil on terminal screen. There is no problem. Why I take this error? Thank you.
Yo need to set the script working directory to the folder where you have your xfoil executable
Hello thank you for the video, can I run it with another airfoil like NACA001X? And if the answer is yes, where can find the data file of the said airfoil?
You can generate maca naca .dat files using XFLR5