An aircraft weighs 6,900 lbs. and has a wing area of 174 sq.ft. on a 35 ft. span. It is cruising at 250 fps. The wing's airfoil has a lift-curve slope of .088 per degree and has a zero-lift angle of -3 degrees. Assume standard sea level conditions. A. Find the induced AOA for an elliptical lift distribution. B. For the real wing, find the actual AOA it is flying at if this wing sweep is 15 degrees. C. For the real wing, find the actual AOA it is flying at if this wing sweep is 38 degrees. D. Calculate the induced drag in pounds, if the Oswald's efficiency is 0.86. E. What would be the induced drag at the same flight conditions if the wing was redesigned with an elliptical lift distribution?