Using Helmbold’s relation for low-aspect-ratio wings, calculate the lift coefficient of a finite wing of aspect ratio 1.5 with an NACA 2412 airfoil section. The wing is at an angle of attack of 5°. Compare this resuit with that obtained from Prandtl’s lifting line theory for high-aspect-ratio wings. Comment on the different between the two results. Assume a span efficiency factor e1 = 1.0.
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