Compute the lift and moment coefficients of a NACA0012 airfoil with a trailing edge flap deflected by 15 degrees at a ge

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answerhappygod
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Compute the lift and moment coefficients of a NACA0012 airfoil with a trailing edge flap deflected by 15 degrees at a ge

Post by answerhappygod »

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.
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