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.

University Physics Volume 1
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ISBN:9781938168277
Author:William Moebs, Samuel J. Ling, Jeff Sanny
Publisher:William Moebs, Samuel J. Ling, Jeff Sanny
Chapter16: Waves
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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 the pressure, density, temperature, velocity, and Mach number downstream of the wave. 
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