the lift L and drag D forces on a NACA 0012 airfoil with the following assumptions. (Note: the C₂
curve passes through zero.)
Standard roughness at Re = 3 million
Operating at 8 degrees angle of attack
Relative wind of 12 m/s,
Chord, c, of 3.5 meter
Span, dr, of 5 meters
Air density of 1.10 kg/m3.
Fig: 1