An airplane with a wing planiform area of 650ft² and a span of 80ft is flying at a density altitude of 38,000ft at a speed of 500mph. The ambient air temperature is 409 ∘R. The gross weight is 52,000lb. Please determine:
(a) Lift Coefficient, C L
​(b) Induced drag in pounds, D i , assuming that the drag due to lift differs from that for the ideal elliptical distribution only by having u=0.99
(c) What is the wing angle of attack, α (above zero lift). Assume η=0.95.