Find mach number-pressure-temperature-before and after shock


Air at a stagnation pressure of 450 Kpa and stagnation temp of 400K flows through a converging nozzle whose throat area is 12 cm^2. Normal shock stands where area is 20cm^2. Compute mach number,pressure,temp- before and after shock.

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Mechanical Engineering: Find mach number-pressure-temperature-before and after shock
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