Aerothermodynamics Research on Cone – cylinder – flare Configuration Reentry Vehicle

JIA  Juhong; HU  Lijie

doi:10.15892/j.cnki.djzdxb.2019.03.024

Journal of Projectiles, Rockets, Missiles and Guidance >

2019 , Vol. 39 >Issue 3: 107 - 110

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2019.03.024

Aerothermodynamics Research on Cone – cylinder – flare Configuration Reentry Vehicle

JIA Juhong ,
HU Lijie

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1 No. 91267 Unit, Fuzhou 350000, China
2 School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China
3 School of Information, Renmin University of China, Beijing 100872, China

Received date: 2018-06-07

Online published: 2025-05-20

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Abstract

There is a shock wave in the outer edge of the spherical head of a hypersonic vehicle, and there is a shock wave-boundary layer interaction on the corner. Then, the aerodynamic heating is a littile complicated. In order to study aerodynamic heating of cone-cylinderflare configuration reentry vehicles, the CFD method was used to study the aerothermodynamics of HIFIRE-4. The results show that, we need to take consideration the aerodynamic heating on nose while in rarefied flow area, for the separation bubble cannot reattach to the flare, and the reattachment heating is not obvious in the corner. But in continuous flow area, there is a change, the separated shock wave reattached to the flare completely, the separation bubble with the gradual narrowing tends to be stable, the aerodynamic heating problems become very prominent.

Key words： cone-cylinder-flare configuration; hypersonic; aerothermodynamics; CFD

Cite this article

JIA Juhong , HU Lijie . Aerothermodynamics Research on Cone – cylinder – flare Configuration Reentry Vehicle[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2019 , 39(3) : 107 -110 . DOI: 10.15892/j.cnki.djzdxb.2019.03.024

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