Reconsider Prob. 17-91. Determine the downstream Mach number, pressure, and temperature below the wedge for a strong oblique shock for an upstream Mach number of 5.
Prob. 17-91
Consider the supersonic flow of air at upstream conditions of 70 kPa and 260 K and a Mach number of 2.4 over a two-dimensional wedge of half-angle 108. If the axis of the wedge is tilted 250 with respect to the upstream air flow, determine the downstream Mach number, pressure, and temperature above the wedge.

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Ma2 Ma = 2.4 25 10