Determine also the duct exit mach number

Reference no: EM131280848

Supersonic airflow enters an adiabatic, constant area (inside diameter = 1 ft) 30-ft-long pipe with Ma1 = 3.0. The pipe friction factor is estimated to be 0.02. What ratio of pipe exit pressure to pipe inlet stagnation pressure would result in a normal shock wave standing at

(a) x = 5 ft, or

(b) x = 10 ft, where x is the distance downstream from the pipe entrance? Determine also the duct exit Mach number and sketch the temperature-entropy diagram for each situation.

Reference no: EM131280848

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Determine also the duct exit mach number : Supersonic airflow enters an adiabatic, constant area (inside diameter = 1 ft) 30-ft-long pipe with Ma1 = 3.0. The pipe friction factor is estimated to be 0.02.

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