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Engineering, 07.08.2019 19:10 tmgoddess2004

You are designing the supersonic nozzle of a small supersonic wind tunnel. if the test section mach number is 3, the test section dimensions 100 mm x 150 mm and the stagnation conditions 600 kpa and 300 k, what is the throat area, exit temperature/pressure and the mass flow rate of the nozzle. let γ = 1.4.

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