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Journal of Projectiles, Rockets, Missiles and Guidance >

2024 , Vol. 44 >Issue 1: 1 - 5

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2024.01.001

Correction of Turbulent Prandtl Number over Hypersonic Flows

  • LIU Jingyuan
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  • Aircraft Engineering College, Nanchang Hangkong University, Nanchang 330063, Jiangxi, China

Received date: 2023-12-11

  Online published: 2024-12-28

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Abstract

To investigate complex non-equilibrium hypersonic shock wave/turbulent boundary layer interaction flows, a turbulent Prandtl number correction model was proposed. The proposed turbulent Prandtl number correction model was evaluated by numerical simulation and theoretical analysis methods to the flows around hypersonic flat plate, compression corners at freestream Mach number 9.22. The comparison of numerical simulation results with experimental data and the Kays’s turbulent Prandtl number model indicates that for hypersonic complex flows, the turbulent Prandtl number should be corrected. The proposed turbulent Prandtl number correction model, which is modified by turbulent non-equilibrium parameters, demonstrates more accurate skin pressure and heat flux compared to the original model and Kays’s model, the maximum wall heat flux relative error is less than 6%.

Key words： hypersonic; shock wave/turbulent boundary layer interaction; aerothermal heating; turbulent Prandtl number; numerical simulation

Cite this article

LIU Jingyuan . Correction of Turbulent Prandtl Number over Hypersonic Flows[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2024 , 44(1) : 1 -5 . DOI: 10.15892/j.cnki.djzdxb.2024.01.001

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