Ah, I am truely dyslexic on the keyboard.
X = (lift)sin(a) - (drag)cos(a) is what I meant to say
I choose ended up going with the NACA 0012, but just out of curiosity... if it is a symmetric airfoil, why is it that programs such as designFOIL and xFOIL generate different lift coefficients for...
Hi Greg,
I guess my question is poorly stated, and does not reveal the the true intent of my investigation.
X = (lift)cos(90-a) - (drag)cos(90-a)
(a = maximum angel of attack)
The angle of attack will be swept through (nearly sinusoidally) from -a -> a, so it would be very nice not to have...
Hey guys,
I'm looking for the airfoil that has the highest lift/drag ratio at the highest possible angle of attack. It would be preferabbly symmetric, even better if it's a NACA 4 digit (or something that would be easy to model).
Any ideas? Thanks in advance :)
