Flat bottom airfoil HELP?

Question

i am doing a angle of attack and lift research on a flat bottom airfoil. i intend to compare my graph result with a thoeretical. how can i find as the formula L = 1/2*v^2*p*a cannot be used to find it. where can i find one. Is lift coefficient is important for this research and what does it shows

Answer 1

The problem with the lift equation is that "coefficient of lift"

Its basically a fudge factor thrown in to make the math equal out to the observations.  CoL changes dramatically depending on many things such as angle of attack and wing plan shape.

Your best bet would be to to get some real observed data off of an existing wing.