Determine the airspeed and the mach number

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Reference no: EM131280957

The stagnation pressure and temperature of air flowing past a probe are 120 kPa(abs) and 100 °C, respectively. The air pressure is 80 kPa(abs). Determine the airspeed and the Mach number considering the flow to be

(a) incompressible,

(b) compressible.

Reference no: EM131280957

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