Consider a normal shock wave at 3 km altitude with a flow Mach number of 2.5 and a pressure ratio, P2/P1 = 3.0 . Find t

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answerhappygod
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Consider a normal shock wave at 3 km altitude with a flow Mach number of 2.5 and a pressure ratio, P2/P1 = 3.0 . Find t

Post by answerhappygod »

Consider a normal shock wave at 3 km altitude with a flow Mach number of 2.5 and a pressure ratio,
P2/P1 = 3.0 . Find the pressure, density, temperature, velocity, and Mach number downstream of the wave.
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