Estimate the mach number and velocity of the flow

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Reference no: EM131369112

A total pressure probe like the one shown in Video V3.8 is inserted into a supersonic airflow. A shock wave forms just upstream of the impact hole. The probe measures a total pressure of 500 kPa(abs). The stagnation temperature at the probe head is 500 K. The static pressure upstream of the shock is measured with a wall tap to be 100 kPa(abs). From these data, estimate the Mach number and velocity of the flow.

Reference no: EM131369112

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