Determine the exit temperature and pressure and mach number

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Reference no: EM131347038

1. Air enters a supersonic isentropic diffuser with a Mach number of 3.00, a temperature of 0.00°C, and a pressure of 1.00 × 10^-2 MPa. Assuming the air exits with negligible velocity, determine the exit temperature, pressure, and mass flow rate per unit inlet area.

2. Propane at 100. kPa 40.0°C is expanded isentropically through a converging-diverging nozzle that has an exit to throat diameter ratio of 2.00. The propane enters with a negligible velocity but reaches sonic velocity at the throat. Determine the exit temperature, pressure, and Mach number, if

(a) the exit pressure is high enough so that the exit velocity is subsonic and

(b) the exit pressure is low enough that the exit velocity is supersonic.

Reference no: EM131347038

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