Two quick questions that you gurus should be able to answer, if not quibble back and forth about:
1. If the slats/flaps are the type that move forward, and aft, of the wing, then does the wing reference area change? (When using the formula L = .5 * rho * V sq * Sref * Cl ) ? Or is the convention to keep the same Sref?
2. With respect to the graph of aoa VS Cl, what is the convention for measuring the aoa? For example 1, consider an aircraft straight and level without slat or flap, and at 5 degrees pitch. Now consider example 2, where the aircraft is slower, still straight and level, but now WITH slat and flap, and at the same 5 degrees pitch. Is the aoa the same for the two examples? After all, the chord angle is now entirely different once slat/flap are added. However, I'm wondering if the chord angle, by convention, is taken in the clean config, and not adjusted for high lift devices?
Hawk