Find the pressure and density

Reference no: EM131466998

Question: The exhaust gases from a rocket engine have a molar mass of 14. They can be assumed to behave as a perfect gas with a specific heat ratio of 1.25. These gases are accelerated through a convergent-divergent nozzle. A normal shock wave occurs in the nozzle at a point in the flow where the Mach number is 2. Find the pressure, temperature, density, and stagnation pressure ratio across this shock wave.

Reference no: EM131466998

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