brilliant! That was clear and concise. I enjoyed the rapid-fire examples as I learned more by the 5 min mark while following along in command prompt, than the last hour of readme files and watching other videos that shows practically nothing. Thanks.
Hi, have you ever encountered a problem where XFOIL converged and generated results for the pressure distribution data (XCp and Cp) and other results from the foil struct as well but not for the polar data (CL,CD,Cm)? When I input a particular coordinates to my XFOIL (in its Matlab interface) it generated all the foil struct just fine including the XCp and Cp, but the CL came out as NaN and other polar struct datas such as CD and Cm came out an empty cell. Can you help me with this? Thanks in advance
This is most often caused by discontinuities in the aerofoil. It can occasionally be a glitch in the matrix. The fix: In the MDES menu, use the FILT command to clean up the shape.
brilliant! That was clear and concise. I enjoyed the rapid-fire examples as I learned more by the 5 min mark while following along in command prompt, than the last hour of readme files and watching other videos that shows practically nothing. Thanks.
Thank you for this useful and concise explanation
Glad it was helpful!
AMAZING video. very informative
Thanks!
Glad it was helpful!
Great explanation! thanks a lot!
Ehi dude, but where's part 2, 3 and so on?
Great video! much appreciated.
Glad it was helpful!
Can you upload another video on xfoil with its detailed capability
Hi, have you ever encountered a problem where XFOIL converged and generated results for the pressure distribution data (XCp and Cp) and other results from the foil struct as well but not for the polar data (CL,CD,Cm)? When I input a particular coordinates to my XFOIL (in its Matlab interface) it generated all the foil struct just fine including the XCp and Cp, but the CL came out as NaN and other polar struct datas such as CD and Cm came out an empty cell. Can you help me with this? Thanks in advance
how to change the x and y range for the polar graft?
Hi what do I do if I get convergence failure when trying to get polars
This is most often caused by discontinuities in the aerofoil. It can occasionally be a glitch in the matrix.
The fix:
In the MDES menu, use the FILT command to clean up the shape.
Great tutorial, if only you had continued and released the next one :/
It's there now, btw