Hi all
As part of our TPE, we would like to determine, using SolidWorks (Flow sim), the lift and drag coefficients of two wing profiles (in this case, a Delta wing of a concorde and that of an ATR 42). Would you be able to tell me if it is possible to create some kind of "polar" for each wing?
Thank you very much, have a good day
Hello
Yes, it is possible to create polars, or even to use existing sources (like: http://airfoiltools.com/airfoil/details?airfoil=oa206-il). You retrieve the X;Y coordinates of the profile in a spreadsheet, you add a Z coordinate (0 for example) and you save your file in .txt format (tab separator, decimal separator the same as solidworks).
Then under solidworks -> insert-->curve --> by x,y,z pts --> browse --> you open your text file.
And there you have it, a curve that can be used as a basis for the construction of your room.
