Air enters a normal shock at 22.6 kPa, 217 K, and 680 m/s. Calculate the stagnation pressure

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Air enters a normal shock at 22.6 kPa, 217 K, and 680 m/s. Calculate the stagnation pressure and Mach number upstream of the shock, as well as pressure, temperature, velocity, Mach number, and stagnation pressure downstream of the shock.
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Thermodynamics An Engineering Approach

ISBN: 978-0073398174

8th edition

Authors: Yunus A. Cengel, Michael A. Boles

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