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In: Mechanical Engineering

A converging-diverging rocket nozzle is connected to a combustion chamber filled with gas at a total...

A converging-diverging rocket nozzle is connected to a combustion chamber filled with gas at a total pressure of 1200 kPa and a total temperature of 2400 K. The design exit Mach number is 2.9 and the nozzle throat area is 50 cm2 . Assume the gas behaves as an ideal gas with k = 1.3 and a molecular weight of 24 kg/kmol. Determine (a) The back pressure necessary to induce the design Mach number at the nozzle exit. (b) The design exit area for isentropic supersonic flow. (c) The static pressure at the throat when the flow is choked. (d) The mass flow rate through the nozzle when the flow is choked.

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I hope you understand. Comment if you have any doubt.

samet mamat answered 3 months ago
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