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Numerical investigation of thermochemical non-equilibrium effects in Mach 10 scramjet nozzle

Published online by Cambridge University Press:  22 May 2024

J.P. Wang Open the ORCID record for J.P. Wang [Opens in a new window] ,
C.F. Zhuo ,
C.L. Dai Open the ORCID record for C.L. Dai [Opens in a new window]  and
B. Sun
J.P. Wang
Affiliation:
School of Mechanical and Engineering, Nanjing University of Science and Technology, Nanjing 210094, China
C.F. Zhuo*
Affiliation:
School of Mechanical and Engineering, Nanjing University of Science and Technology, Nanjing 210094, China
C.L. Dai
Affiliation:
School of Mechanical and Engineering, Nanjing University of Science and Technology, Nanjing 210094, China
B. Sun
Affiliation:
School of Mechanical and Engineering, Nanjing University of Science and Technology, Nanjing 210094, China
*
Corresponding author: C.F. Zhuo; Email: njust203zcf@126.com
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Abstract

High-temperature non-equilibrium effects are prominent in scramjet nozzle flows at high Mach numbers. Hence, the thermochemical non-equilibrium gas model incorporating the vibrational relaxation process of molecules in the hydrocarbon-air reaction is developed to numerically simulate the flow of a hydrocarbon fuel scramjet nozzle at Mach 10. Besides, the results computed by the models of the thermally perfect gas, chemically non-equilibrium gas, and thermally non-equilibrium chemically frozen gas are applied for comparative studies. Results indicate that chemical non-equilibrium effects are more significant for the flow-field structure and parameters compared to thermal non-equilibrium effects. Meanwhile, vibrational relaxation and chemical reactions interact in the flow-field. The heat released from the chemical reactions in the flow-field of the thermochemical non-equilibrium gas model makes the thermal non-equilibrium effects weaker compared to the thermally non-equilibrium chemically frozen gas model; the chemical reactions in the thermochemical non-equilibrium gas model are more intense than in the chemically non-equilibrium gas model. Due to the slow relaxation of vibrational energy, the thermal non-equilibrium models predicted nozzle thrust lower than the thermal equilibrium models by approximately 1.11% to 1.33%; when considering the chemical reactions, the chemical non-equilibrium models predicted nozzle thrust higher than the chemical frozen models by approximately 7.30% to 7.54%. Hence, the structural design and performance study of the high Mach numbers scramjet nozzle must consider thermochemical non-equilibrium effects.

Keywords

hydrocarbon fuelMach 10 scramjet nozzlethermochemical non-equilibrium gashigh temperaturenozzle performance
Type
Research Article
Information
The Aeronautical Journal , First View , pp. 1 - 18
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Copyright
© The Author(s), 2024. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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