calculate downstream Mach number Ma2 and pressure P2.

Prandtl–Meyer Expansion Wave Calculations

Supersonic air at Ma1 = 2.0 and 230 kPa flows parallel to a flat wall that suddenly expands by δ = 10° (Fig. 17–49). Ignoring any effects caused by the boundary layer along the wall, calculate downstream Mach number Ma2 and pressure P2.


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