the wing of a light single-engine general


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.

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Mechanical Engineering: the wing of a light single-engine general
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