Assuming level flight with elevators slightly up and flaps slightly down, how much (order of magnitude) is the actual AoA of a typical, flapped stunt wing?
Peter Germann
Figure the Cl is about .1 per degree, solve the lift equation for Cl, should get you pretty close.
f=1/2*Cl*rho*A*v^2
2*f/(rho*A*v^2)=Cl (f/a= wing loading)
putting in my airplane as an example
f=4 lb, a=4.61 sq feet, rhos = 0.0023 lb/ft^3, v=80 ft/sec
Cl=0.12 degrees, so about 1.2 degrees. Some of that is taken out with flap deflection, so, maybe the fuselage is about 0.5-0.6 degrees or so .
Brett