Let's explore the effects of changing the position of the peak thickness of the airfoil. The standard NACA 00xx airfoils have the peak thickness at about the 30% point. What happens if this point is moved forward or aft. My theory is the further forward this point is (up to a certain point) the higher the drag but the smoother and more stable the wing will be during changing AoA manuevers (i.e. 3D stuff).

Ollie, any thoughts?