Determine the upstream and downstream mach numbers

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Reference no: EM131347006

1. The upstream and downstream isentropic stagnation pressures across a normal shock wave in air are measured and found to be 124.6801 kPa and 0.101325 MPa, respectively. Determine the upstream and downstream Mach numbers and static pressure and temperature ratios across the shock wave.

2. A converging-diverging nozzle has an exit to throat area ratio of 2.00. The inlet isentropic stagnation air pressure is 2.00 atm and the exit static pressure is 1.00 atm. This flow is supersonic in a portion of the nozzle, terminating in a normal shock inside the nozzle. Determine the local area ratio A/A*at which the shock occurs.

Reference no: EM131347006

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