Find stagnation pressure and mach number of flow


You are designing a converging-diverging nozzle to operate at sea level. The nozzle will be mounted on a glider that flies at 60 mph. The entrance to the nozzle is 1 m^2. What is the stagnation pressure and Mach number of flow entering nozzle? What should throat and exit area be if exit mach number is 2?

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Mechanical Engineering: Find stagnation pressure and mach number of flow
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