Consider an infinite-span wing with a NACA 0006 airfoil section and a chord length of 1 m. The wing is at an angle of attack of 4°.

a. Estimate the wing lift and drag per unit span in airflow with velocity 50 m/s at standard sealevel conditions.
b. If the same wing is flying at an altitude 5 km with velocity 200 m/s, what is the lift per unit span?
c. Now consider a finite-span wing with the same profile, chord and attack angle flying at 5 km altitude with a speed of 50 m/s. The wing aspect ratio is 5, area is 5 m^2 , and span efficiency factor is 0.9. Determine the wing lift.

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Explanation: