Xavier Garcia

Wow it's great! Using your file I can run it! I did reinstall it many times but I assume then it's something with the settings I suppose (even that I checked many times). Many many thanks Stefan! Thanks again, Xavier

Actually no errros, just that the analysis says that Cl is 0 along all the wingspan if I chose that airfoil instead of a NACA

Hi Stefan, I know that the polars for every airfoil work, but are also the whole plane and wing analysis working for you? Because I have been trying with a Windows PC and its not working either. You can check it by seeing the distribution of Cl along the wingspan being 0. If yours is working, could you send the file so I can try on other PCs? Thanks a lot, Xavier

Oh sorry, my mistake. Here you go! Thanks to look at it in advance Stefan!

The problem is that I can perfectly run all the imported airfoil analysis, but when I analyze a wing with that same airfoil it just appears to be a flat plate, as the local lift is 0 everywhere. But, if I do the same wing analysis using a NACA airfoil generated by XFLR5, works perfect, I would like to perform the wing analysis with the imported airfoils. Does someone know how to deal with this bug? Thank you very much! Here you can find my file: