Consider the North American P-51D Mustang shown in Fig. 4.39. Its wingspan is 37 ft, wing...

Consider the North American P-51D Mustang shown in Fig. 4.39. Its wingspan is 37 ft, wing area is 233.6 ft2 and gross weight is 10,100 lb. Assume the Oswald efficiency factor is 0.8. The airplane is flying in steady level flight at a velocity of 300 mph at a standard altitude of 5000 ft. Calculate the drag due to lift using (a) the result of Problem 6.28, and (b) the coefficient of drag due to lift, CD i. The two results should be the same.

Figure 6.39 Determination of absolute and service ceilings for the CJ-1.