Find the new mass flow rate and exit mach number

Reference no: EM131347051

1. Air at 150. kPa 100.°C enters a converging nozzle with a negligible velocity and is expanded isentropically until the exit pressure reaches 101 kPa. Determine the exit Mach number and temperature.

2. 1.86 kg/s of air flows through a converging-diverging supersonic wind tunnel whose reservoir isentropic stagnation conditions are 18.0 atm at 300. K and whose exit Mach number is 4.80. If the reservoir isentropic stagnation pressure is raised to 20.0 atm at the same temperature, find the new mass flow rate and exit Mach number if the exit pressure remains constant.

Reference no: EM131347051

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