Find the temperature and pressure on the exit plane of duct

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Reference no: EM131467219

Question: Air with a stagnation pressure of 600 kPa and a stagnation temperature of 150°C flows through a convergent-divergent nozzle, the Mach number being greater than 1 at the nozzle exit. The throat area of the nozzle is 1 cm2. The flow from the nozzle enters a duct that has a constant area of 3 cm2. If the flow in the nozzle can be assumed to be isentropic and if the flow in the duct can be assumed to be adiabatic and if the mean friction factor is 0.004, find the temperature and the pressure on the exit plane of the duct.

Reference no: EM131467219

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