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5. Using the Lift and Drag curves for the NACA 4412 airfoils included with this assignment, calculate

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