Compute the lift and moment coefficients of a NACA0012 airfoil with a trailing edge flap deflected by 15 degrees at a ge
Posted: Sat May 21, 2022 10:18 am
Compute the lift and moment coefficients of a NACA0012 airfoil
with a trailing edge flap deflected by 15 degrees at a geometric
angle of attack of 3 degrees. The flap dimension is 20% of the
airfoil chord.
with a trailing edge flap deflected by 15 degrees at a geometric
angle of attack of 3 degrees. The flap dimension is 20% of the
airfoil chord.