Consider the Lockheed-Martin F-16 described in Problem 6.31. Assume that the photograph in Fig. 6.56 was taken when the airplane is climbing vertically at the instant it is passing through an altitude of2000 m with a velocity of 100m/sec. Calculate the maximum acceleration of the airplane at that instant. Problem 6.31. The Lockheed-Martin F-16 is shown in Fig. 6.56 in a vertical accelerated climb. Some characteristics of this airplane from Jane’s All the World Aircraft are: Wing area = 27.87 m2, typical combat weight= 8,273 kg,, sea-level static thrust from the single GE jet engine = 131.6 . (Note that Jane’s quotes the weight in units of kilogram force; see Sec. 2.4 for a discussion of this unit.) Assume that the subsonic value of the zero-drag coefficient is 0.016 (consistent with the data shown in Fig. 6.77). Also assume that the transonic value of the zero-lift drag coefficient at Mach one is 2.3 times its subsonic value, a typical increase that occurs in the drag-divergence transonic flight region. For these conditions, is it possible for the F-16 to break the speed of sound going straight up?
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