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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Transcribed Image Text: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
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