Calculate the lift and induced drag coefficients

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Reference no: EM131515238

Question: 1. The spanwise distribution of circulation along an untwisted rectangular wing of aspect ratio 5 can be written in the form

Γ = 2svα[0.02340sinΘ + 0.00268 sin3Θ + 0.00072 sin5Θ + 0.00010 sin7Θ]

Calculate the lift and induced drag coefficients when the incidence α measured to no lift is 10? .

2. An airplane weighing 250 kN has a span of 34 m and is flying at 40 m/s with its tailplane level with its wings and at height 6.1 m above the ground. Estimate the change due to ground effect in the downwash angle at the tailplane, which is 18.3 m behind the center of pressure of the wing.

Reference no: EM131515238

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