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The wing of a light, single-engine general aviation aircraft has an area of 15.8 m2 and a span of 9.6 m. The airfoil of the wing is NACA 65-415, which has a lift slope of 0.1033 per degree and zero-lift angle of attack of -3o. Assume the span efficiency factor of 0.893.
a. If the wing is to produce 11 kN lift while cruising at 190 km/h at standard sea level, calculate the geometric angle of attack that the wing should be set to.
b. Calculate also the induced drag experienced by the wing in that condition.
lame''s theorem
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