Q1) Air flows over a plane wall at a Mach number 3.5, the pressure in the flow being 100kpa. The wall turns through an downstream of the that the pressure angle leading to generation of an oblique shock wave whose strength is such corner is 548kpa. Find the turning angle of corner.

Q: Mach number

A: M=1.005 P/Pt = 0.561

Q: What is the area where the shock appears? Calculate (b) the pressure and (c) the temperature…

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