A symmetric converging-diverging nozzle with an area ratio of 2 encounters a 700 m/s flow of air at 50 kPa and 27oC.
From the same turbojet engine, supersonic air at Mach 3 and 75 kPa impinges on a two-dimensional wedge of half-angle 10o. 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
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