B. An airplane with a wing area of 450ft2 and a span of 70ft is flying at a pressure altitude of 8000ft at a speed of 280mph. The pressure is 1572.1lb/ft2 and the ambient temperature is 490.17R. The wing has a geometric angle of attack of 4 degrees above the angle for zero lifts. Assume the two-dimensional lift curve slope is 95% of the theoretical value. Determine: a. Lift in pounds b. The induced drag coefficient. Assume that the drag due to lift differs from that for the ideal elliptical distribution only by having u=0.98. c. The induced drag in pounds d. The lift to induced drag ratio