I am doing a project attempting to determine the increase in lift and drag coefficients of an airfoil as the angle of its flap increases. In my research, I have found the thin airfoil with flap approximation in Mechanics of Flight:
However, this is a plain flap and not one for a slotted flap. Similarly, I basically cannot find anything on formulas that determine the drag coefficient with a flap deflection.
Of course, I am aware of the DATCOM methods, but I will need something physics-based.
Any help will be appreciated.