Compute the lift and moment coefficients of a NACA0012 airfoil with a trailing edge flap deflected by 18 degrees at a ge
Posted: Sat May 21, 2022 10:20 am
Compute the lift and moment coefficients of a NACA0012 airfoil with a trailing edge flap deflected by 18 degrees at a geometric angle of attack of 5 degrees. The flap dimension is 25% of the airfoil chord.