Question

Consider a finite wing of aspect ratio 4 with an NACA 2412 airfoil; the angle of attack is 5°. Calculate (a) the lift coefficeint at low speeds (incompressible flow) using the results of Prandtl's lifting line theory, and (b) the lift coefficient for M00 = 0.7. Assume that the span efficiency factor for lift is e1 = 0.90.

Answer 1

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