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Air enters, a normal shock at 18 kPa, 205 K, and 740 m/s.

Chapter 12, Problem 64P

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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,

                                                                    

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