Norman
Well-Known Member
I'm consulting on some modifications to a swept wing motor glider. One mod being considered is the addition of vortilons. Unfortunately there doesn't seam to be much published about how to do it (not that I can get easily anyway). As I understand it the idea is to block the spanwise flow of the leading edge stagnation point at or just before the stall AoA. So if I have the pressure distribution at the critical AoA my guess is that the stagnation point is at the point of highest pressure and the upwash angle is perpendicular to the surface at that spot. Am I right about that? If not could somebody give me a clue?
