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Influence of high temperature non-equilibrium effects on Mach 12 scramjet inlet

文献类型：期刊论文

作者Dai, Chunliang3; Sun, Bo3; Zhou, Shengbing2; Zhuo, Changfei3; Zhou, Changsheng3; Yue, Lianjie1; Yue LJ(岳连捷)
刊名ACTA ASTRONAUTICA
出版日期2022-04-01
卷号193页码:237-254
ISSN号0094-5765
关键词Mach 12 scramjet inlet High temperature Non-equilibrium effects Thermochemical Inlet performance
DOI10.1016/j.actaastro.2022.01.013
通讯作者Sun, Bo(hypersun@126.com)
英文摘要To better understand the high temperature non-equilibrium effects of a high Mach number (above Mach 8) scramjet inlet, the thermal and chemical non-equilibrium flow of Mach 12 two-dimensional inlet is numerically analyzed by using the thermochemical non-equilibrium gas model including a two-temperature model and air chemical reactions. The thermal equilibrium flow is simulated by using the models of thermally perfect gas and chemical non-equilibrium gas. It is found that the thermal non-equilibrium effects are relatively strong near the cowl shock and in the outer layer of the boundary layer, and gradually weaken in the downstream zone of the cowl shock. The chemical non-equilibrium effects and thermal equilibrium flows mainly exist in the high-temperature region of the boundary layer. Compared with the chemical non-equilibrium gas, the oxygen dissociation reaction near the lower wall for the thermochemical non-equilibrium gas is weaker in the external compression section; It is stronger due to fully excited vibration energy, in the internal compression section. Compared with the other models, the inlet compression ability for the thermochemical non-equilibrium gas is higher, the coefficient of mass flow and total pressure recovery for it are lower. Hence, the high temperature non-equilibrium effects can not be ignored in the design of the high Mach number scramjet inlet.
WOS关键词VIBRATIONAL NONEQUILIBRIUM ; FLAME STABILIZATION ; ROTATING DETONATION ; COMBUSTOR ; ETHYLENE ; PERFORMANCE ; DESIGN ; TUNNEL ; FIELD ; FLOW
资助项目Postgraduate Research & Practice Innovation Program of Jiangsu Province[KYCX21_0338] ; China Postdoctoral Science Foundation[BX20200070] ; Opening Foundation of National State Key Laboratory of High Temperature Gas Dynamics
WOS研究方向Engineering
语种英语
WOS记录号WOS:000772023900021
资助机构Postgraduate Research & Practice Innovation Program of Jiangsu Province ; China Postdoctoral Science Foundation ; Opening Foundation of National State Key Laboratory of High Temperature Gas Dynamics
源URL[http://dspace.imech.ac.cn/handle/311007/88790]  
专题力学研究所_高温气体动力学国家重点实验室
通讯作者Sun, Bo
作者单位1.Chinese Acad Sci, State Key Lab High Temp Gas Dynam, Inst Mech, Beijing 100190, Peoples R China
2.Chongqing Univ, Coll Aerosp Engn, Chongqing 400044, Peoples R China
3.Nanjing Univ Sci & Technol, Sch Mech Engn, Nanjing 210094, Peoples R China
推荐引用方式
GB/T 7714		 Dai, Chunliang,Sun, Bo,Zhou, Shengbing,et al. Influence of high temperature non-equilibrium effects on Mach 12 scramjet inlet[J]. ACTA ASTRONAUTICA,2022,193:237-254.
APA Dai, Chunliang.,Sun, Bo.,Zhou, Shengbing.,Zhuo, Changfei.,Zhou, Changsheng.,...&岳连捷.(2022).Influence of high temperature non-equilibrium effects on Mach 12 scramjet inlet.ACTA ASTRONAUTICA,193,237-254.
MLA Dai, Chunliang,et al."Influence of high temperature non-equilibrium effects on Mach 12 scramjet inlet".ACTA ASTRONAUTICA 193(2022):237-254.

入库方式： OAI收割

来源：力学研究所

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