I am planning to use flaps on my plane which is to be flown in the advanced class section of the SAE aero design Competition. I am having troubles finding out the lift produced by the deflecting the flaps for say 30 deg. I wanna find out the method to find the new Cl max for the wing after the flaps are deflected. I tried to analyze the airfoil with flaps installed in XFLR and Avl.... But i wanna make sure because I m getting values of Cl like 2 at 30 deg with 5 deg incidence. Any help is appreciated.