Mitek,

I like to look at wings(foils) in terms of absolute AOA....and All planes have to fly with a positive absolute AOA (if it was zero then we would be generating no lift). At, 10 degree absolute AOA you get into the beginning of stall and at absolute AOA of about 15 degrees you are at max Cl and shortly there after you are stalled.

To change the foil cl to the Cl.... the three diminsionsal form, use the following equation:

Cl=cl/(1+(cl/(Pi*AR*e)))

ex:
AR=3
e=1
cl=1.5

Cl=1.5/(1+(1.5/9.42)
Cl=1.5/1+.16
Cl=1.29

Have you checked out
[link]http://www.grc.nasa.gov/WWW/K-12/airplane/foil2.html[/link]This has the AR correction in it and you can try out different shaped foils,speed,AR and see how they effect things.


Steve