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Air enters a converging-diverging nozzle of a supersonic wind tunnel at 1 MPa and 37 ºC with a low velocity. The flow area of the test section is equal to the exit area of the nozzle, which is 0,5m2.
Calculate the pressure, temperature, velocity, and mass flow rate in the test section for a Mach number Ma = 2. Explain why the air must be very dry for this application.
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What is the total rate of heat transfer to the air? What is the pressure drop associated with the airflow?
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