tasesq:

Questions are never stupid.

You could start reading this, learning and trying to figure it out:

http://en.wikipedia.org/wiki/NACA_airfoil

Different % up and down means the airfoils at the points 1, 3 and 4 of the wing have some camber (non-symetrical).

Just calculate the camber for those and ask Profili plotting them for you. [sm=spinnyeyes.gif]

Regards!