Standing oblique detonation for hypersonic propulsion: A review

doi:10.1016/j.paerosci.2023.100955

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

	Standing oblique detonation for hypersonic propulsion: A review
	Jiang ZL(姜宗林)
刊名	PROGRESS IN AEROSPACE SCIENCES
	2023-11-01
卷号	143 页码:17
关键词	Standing oblique detonation Scramjet engine Oblique detonation engine Shock wave Supersonic combustion Hypersonic ramjet propulsion
ISSN号	0376-0421
DOI	10.1016/j.paerosci.2023.100955
通讯作者	Jiang, Zonglin(zljiang@imech.ac.cn)
英文摘要	Standing oblique detonation is a unique pressure-gain combustion phenomenon for hypersonic ramjet propulsion, and its research has been related with supersonic combustion in scramjet engines since its births, for example, absent treatment in its early stage and re-consideration in recent decades. Standing oblique detonations and supersonic combustion share the same features of supersonic chemically-reacting flows, and can be considered as different flow development stages. Combustion instability in a chemically-reacting flow is reviewed first to identify its fundamental mechanisms, and the upstream-propagating shock wave is identified as one of intrinsic characteristics and taken as the key problem for developing hypersonic ramjet propulsion. Critical conditions for the standing oblique detonation are summarized as a theoretical base for standing oblique detonation ramjet engines. Three key parameters are included, that is, the maximum heat that can drive local flow states from supersonic to sonic after combustion, the critical inflow Mach number of combustors, at which supersonic combustion becomes stable, and the critical wedge angle at which a standing oblique detonation can be initiated. The evolution of the standing oblique detonation is reviewed by placing emphasis on its complex wave structure that was found to develop via three stages, that is, shock-induced initiation, the decaying stage and the fully-developed stage. Finally, progress in experimental research is reviewed with detailed discussions on stabilization of the standing oblique detonation, experimental methods and development of adequate test facilities. In conclusion, the stable operation of hypersonic ramjet propulsion is a critical issue to approach its engineering application, and the standing oblique detonation ramjet engine is recommended as a promising candidate, deserving more attention in the future.
分类号	一类
资助项目	National Natural Science Foundation of China[11532014] ; National Natural Science Foundation of China[11727901] ; National Natural Science Foundation of China[12132017]
WOS关键词	WAVES ; WEDGE ; SHOCK ; CRITERIA
WOS研究方向	Engineering
语种	英语
WOS记录号	WOS:001138629400001
资助机构	National Natural Science Foundation of China
其他责任者	Jiang, Zonglin
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/94243]
专题	力学研究所_高温气体动力学国家重点实验室
推荐引用方式 GB/T 7714	Jiang ZL. Standing oblique detonation for hypersonic propulsion: A review[J]. PROGRESS IN AEROSPACE SCIENCES,2023,143:17.
APA	姜宗林.(2023).Standing oblique detonation for hypersonic propulsion: A review.PROGRESS IN AEROSPACE SCIENCES,143,17.
MLA	姜宗林."Standing oblique detonation for hypersonic propulsion: A review".PROGRESS IN AEROSPACE SCIENCES 143(2023):17.