Air flowing steadily in a nozzle experiences a normal shock at a Mach number of Ma =

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Air flowing steadily in a nozzle experiences a normal shock at a Mach number of Ma = 2.5. If the pressure and temperature of air are 10.0 psia and 440.5 R, respectively, upstream of the shock, calculate the pressure, temperature, velocity, Mach number, and stagnation pressure downstream of the shock. Compare these results to those for helium undergoing a normal shock under the same
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Thermodynamics An Engineering Approach

ISBN: 978-0073398174

8th edition

Authors: Yunus A. Cengel, Michael A. Boles

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