Oblique detonation wave triggered by a double wedge in hypersonic flow

doi:10.1016/j.cja.2021.07.040

	Oblique detonation wave triggered by a double wedge in hypersonic flow
	Teng, Honghui1 ; Zhang, Yuhang 1; Yang PF(杨鹏飞)2,3; Jiang ZL(姜宗林)2,3
通讯作者	Yang, Pengfei(young1505@foxmail.com)
发表期刊	CHINESE JOURNAL OF AERONAUTICS
	2022-04-01
卷号	35 期号:4 页码:176-184
ISSN	1000-9361
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.
关键词	Double wedge Hypersonic flow Initiation structures Oblique detonation Shock interactions
DOI	10.1016/j.cja.2021.07.040
收录类别	SCI ; EI ; CSCD
语种	英语
WOS记录号	WOS:000794041600002
关键词[WOS]	SHOCK-WAVES ; NUMERICAL-SIMULATION ; OXYGEN MIXTURES ; MACH NUMBER ; COMBUSTION ; TRANSITION ; INITIATION ; PERFORMANCE
WOS研究方向	Engineering
WOS类目	Engineering, Aerospace
资助项目	National Natural Science Foundation of China[11822202]
项目资助者	National Natural Science Foundation of China
论文分区	一类
力学所作者排名	1
RpAuthor	Yang, Pengfei
引用统计	被引频次：17[WOS] [WOS记录] [WOS相关记录]
文献类型	期刊论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/89457
专题	高温气体动力学国家重点实验室
作者单位	1.Beijing Inst Technol, Sch Aerosp Engn, Beijing 100081, Peoples R China; 2.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China; 3.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China
推荐引用方式 GB/T 7714	Teng, Honghui,Zhang, Yuhang,Yang PF,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,杨鹏飞,&姜宗林.(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.

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