Question: Problem 4. Airflow at Ma = 3.2 is turned through an angle of 25 as a result of flowing through an oblique shock having

Problem 4. Airflow at Ma = 3.2 is turned through an angle

Problem 4. Airflow at Ma = 3.2 is turned through an angle of 25 as a result of flowing through an oblique shock having a shock angle 1 (> 25). What isentropic expansion turn is required to bring the flow back to (i) its original Mach number? (ii) its original pressure?

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