Question

A symmetric converging-diverging nozzle with an area ratio of 2
encounters a 700 m/s flow of air at 50 kPa and 27^{o}C.

From the same turbojet engine, supersonic air at Mach 3 and 75
kPa impinges on a two-dimensional wedge of half-angle
10^{o}. Determine the following:

a. The two possible oblique shock angles that could be formed by this wedge

b. The pressure downstream of the oblique shock for each case

c. The Mach number downstream of the oblique shock for each case

Answer #1

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