Oblique detonation wave triggered by a double wedge in hypersonic flow

doi:10.1016/j.cja.2021.07.040

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

	Oblique detonation wave triggered by a double wedge in hypersonic flow
	Teng, Honghui 3; Zhang, Yuhang 3; Yang, Pengfei 1,2; Jiang, Zonglin 1,2
刊名	CHINESE JOURNAL OF AERONAUTICS
	2022-04-01
卷号	35 期号:4 页码:176-184
关键词	Double wedge Hypersonic flow Initiation structures Oblique detonation Shock interactions
ISSN号	1000-9361
DOI	10.1016/j.cja.2021.07.040
通讯作者	Yang, Pengfei(young1505@foxmail.com)
英文摘要	Pressure-gain combustion has gained attention for airbreathing ramjet engine applications owing to its better thermodynamic efficiency and fuel consumption rate. In contrast with traditional detonation induced by a single wedge, the present study considers oblique shock interactions attached to double wedges in a hypersonic combustible flow. The temperature/pressure increases sharply across the interaction zone that initiates an exothermic reaction, finally resulting in an Oblique Detonation Wave (ODW). Compared with the case for a single-wedge ODW, the double-wedge geometry has great potential to control the initiation of the ODW. As a tentative study, two-dimensional compressible Euler equations with a two-step induction-reaction kinetic model are used to solve the detonation dynamics triggered by a double wedge. The effects of the wedge angles and wedge corner locations on the initiation structures are investigated numerically. The results show an ODW complex comprising three Oblique Shock Waves (OSWs), an induction zone, a curved detonation front, and an unburned/low-temperature gas belt close to the surface of the second wedge. Both the increasing wedge angle and downstream wedge corner location lead to an abrupt OSW-ODW transition type, whereas the former corresponds to the shock-shock interaction and the later has a greater effect on the exothermic chemical process. Analysis of the shock polar and flow scale confirms that the OSW-ODW initiation structure mainly depends on the coupling of shocks and heat release in a confined initiation zone. (C) 2021 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd.
资助项目	National Natural Science Foundation of China[11822202]
WOS关键词	SHOCK-WAVES ; NUMERICAL-SIMULATION ; OXYGEN MIXTURES ; MACH NUMBER ; COMBUSTION ; TRANSITION ; INITIATION ; PERFORMANCE
WOS研究方向	Engineering
语种	英语
WOS记录号	WOS:000794041600002
资助机构	National Natural Science Foundation of China
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/89456]
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	Yang, Pengfei
作者单位	1.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China 2.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China 3.Beijing Inst Technol, Sch Aerosp Engn, Beijing 100081, Peoples R China
推荐引用方式 GB/T 7714	Teng, Honghui,Zhang, Yuhang,Yang, Pengfei,et al. Oblique detonation wave triggered by a double wedge in hypersonic flow[J]. CHINESE JOURNAL OF AERONAUTICS,2022,35(4):176-184.
APA	Teng, Honghui,Zhang, Yuhang,Yang, Pengfei,&Jiang, Zonglin.(2022).Oblique detonation wave triggered by a double wedge in hypersonic flow.CHINESE JOURNAL OF AERONAUTICS,35(4),176-184.
MLA	Teng, Honghui,et al."Oblique detonation wave triggered by a double wedge in hypersonic flow".CHINESE JOURNAL OF AERONAUTICS 35.4(2022):176-184.