Thread: Discussion Airfoil Optimization with XFOIL
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Old May 25, 2010, 04:45 PM
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Originally Posted by Montag DP View Post
Yes, that would be possible. It wouldn't be guaranteed to get better results than what you already have because of the limitations of the parameters and the constraints I place on them. I will probably at least relax the constraint on max camber, though.

Another difficulty is that max Cl occurs right before stall, which is not always at the same angle of attack. It should be possible to do it, though, with a little bit of tweaking.

Well, I guess the way to do it is to test each airfoil at a range of AoA, and select the best for that airfoil.

I would certainly remove the max camber constraint. Remember, the purpose is simply to achieve the maximum lift, at the expense of everything else. Although I think there should be a fixed chord and Re (my personal preference being 20cm and 35000, but could be anything).

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