A rocket engine can generate hot gas conditions at the exit of the combustion chamber Po= 100 atm, To = 3000K at a mass flow rate of 500 kg/s. The rocket nozzle will be designed so that the exhaust flow is perfectly expanded at an altitude of 15,000 m, where ambient pressure Pamb = 12.04 kPa. For the nozzle design, determine the following a) Throat area At (m²) b) Exit area Ae (m²) c) Thrust at the design condition (kN) Assume isentropic flow in the nozzle with gas properties of combustion products Specific gas constant R = 594 J/kg K, y = 1.2

A rocket engine can generate hot gas conditions at the exit of the combustion chamber Po= 100 atm, To = 3000K at a mass flow rate of 500 kg/s. The rocket nozzle will be designed so that the exhaust flow is perfectly expanded at an altitude of 15,000 m, where ambient pressure Pamb = 12.04 kPa. For the nozzle design, determine the following a) Throat area At (m²) b) Exit area Ae (m²) c) Thrust at the design condition (kN) Assume isentropic flow in the nozzle with gas properties of combustion products Specific gas constant R = 594 J/kg K, y = 1.2

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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