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A supersonic airflow at M=3.5 and P=100 kPa absolute undergoes a normal shock. Calculate: a) Mach number after the shock, M2, b) The total

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A supersonic airflow at M=3.5 and P=100 kPa absolute undergoes a normal shock. Calculate: a) Mach number after the shock, M2, b) The total pressure after the shock, P.2.

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