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Air enters, a normal shock at 18 kPa, 205 K, and 740 m/s.
Chapter 12, Problem 64P(choose chapter or problem)
QUESTION:
Problem 64P
Air enters, a normal shock at 18 kPa, 205 K, and 740 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.
Questions & Answers
QUESTION:
Problem 64P
Air enters, a normal shock at 18 kPa, 205 K, and 740 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.
ANSWER:
Step 1 of 7
The Mach number of upstream is calculated as,