Thermochemical non-equilibrium effects on hypersonic shock wave/turbulent boundary-layer interaction

doi:10.1016/j.actaastro.2021.12.010

CORC > 力学研究所 > 中国科学院力学研究所 > 高温气体动力学国家重点实验室

	Thermochemical non-equilibrium effects on hypersonic shock wave/turbulent boundary-layer interaction
	Jiang, Hao 2; Liu, Jun 2; Luo, Shichao 2; Huang, Wei 2; Wang, Junyuan 2; Liu MK(刘美宽)1
刊名	ACTA ASTRONAUTICA
	2022-03-01
卷号	192 页码:1-14
关键词	Hypersonic flow Shock wave/turbulent boundary-layer interactions Thermochemical non-equilibrium Turbulence model
ISSN号	0094-5765
DOI	10.1016/j.actaastro.2021.12.010
通讯作者	Liu, Jun(liujun@nudt.edu.cn)
英文摘要	The research on shock wave/turbulent boundary-layer interactions is mainly limited to calorically perfect gases; little has been reported on the thermochemical non-equilibrium (real gas) effect. This effect is prominent at conditions of high Mach and Reynolds numbers. In this work, a household parallel solver for hypersonic thermochemical non-equilibrium flows with a Reynolds-averaged Navier-Stokes turbulence model is developed in which the coupling of turbulence with vibration and chemistry occurs under a gradient-law assumption. The thermal non-equilibrium is based on Park's two-temperature model, and the chemical non-equilibrium is based on Gupta's 11-species model. The method proposed in this paper is first validated using experimental data, including cases of a laminar cylinder flow at a high-enthalpy condition, a supersonic flat-plate turbulent boundary layer flow, a hypersonic transition flow, and a hypersonic compression corner flow at a low-enthalpy condition. This approach is then applied to assess the hypersonic flow characteristics past the 34 degrees compression corner at a flight height of 30 km. Results show that the joint effects of turbulence and thermochemical non-equilibrium have a significant impact on the flow field organization, wall data, and separation length of the shock wave/boundary-layer interaction. Furthermore, the mechanism of the neck region accompanied by maximum heat flux, wall pressure and skin friction in both laminar and turbulent cases is well-interpreted. This study can be used as a reference tool for the aerodynamic design of future hypersonic vehicles accounting for multi-physics effects.
分类号	二类/Q1
资助项目	National Key R&D Program of China[2019YFA0405300] ; National Key R&D Program of China[2019YFA0405203] ; Natural Science Foundation of Hunan Province of China[2020JJ4656] ; National Natural Science Foundation of China[11702322]
WOS关键词	TURBULENCE MODELS ; NUMERICAL-SIMULATION ; THERMAL PROTECTION ; FLOW ; PREDICTION ; MECHANISM ; LAMINAR
WOS研究方向	Engineering
语种	英语
WOS记录号	WOS:000772023700001
资助机构	National Key R&D Program of China ; Natural Science Foundation of Hunan Province of China ; National Natural Science Foundation of China
其他责任者	Liu, Jun
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/88802]
专题	力学研究所_高温气体动力学国家重点实验室
作者单位	1.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China 2.Natl Univ Def Technol, Sci & Technol Scramjet Lab, Changsha 410073, Peoples R China;
推荐引用方式 GB/T 7714	Jiang, Hao,Liu, Jun,Luo, Shichao,et al. Thermochemical non-equilibrium effects on hypersonic shock wave/turbulent boundary-layer interaction[J]. ACTA ASTRONAUTICA,2022,192:1-14.
APA	Jiang, Hao,Liu, Jun,Luo, Shichao,Huang, Wei,Wang, Junyuan,&刘美宽.(2022).Thermochemical non-equilibrium effects on hypersonic shock wave/turbulent boundary-layer interaction.ACTA ASTRONAUTICA,192,1-14.
MLA	Jiang, Hao,et al."Thermochemical non-equilibrium effects on hypersonic shock wave/turbulent boundary-layer interaction".ACTA ASTRONAUTICA 192(2022):1-14.