Study on the propulsive performance of oblique detonation engine

doi:10.1016/j.energy.2024.130519

	Study on the propulsive performance of oblique detonation engine
	Liu YF(刘云峰)1 ; Han, Xin2 ; Zhang, Zijian 3
通讯作者	Liu, Yunfeng(liuyunfeng@imech.ac.cn)
发表期刊	ENERGY
	2024-04-01
卷号	292 页码:11
ISSN	0360-5442
摘要	The oblique detonation engine (ODE) has established a clear superiority for hypersonic flight because of its high thermal efficiency and compact structure. It has become the research hot spot all over the world in recent years. The aim of this study is to derive a criterion on the propulsive balance of ODE, from which we can find the key parameters governing the propulsive performance explicitly. A physical model of ODE is put forth, which consists of the inlet, the constant cross-section combustor and the divergent nozzle. The mathematical equations to calculate the thrust generated by the divergent nozzle and the pressure drag produced by the inlet are deduced. The net thrust of ODE is then obtained. The criterion shows clearly that the static temperature at the engine inlet exit is a very important parameter. The lower the inlet exit temperature is, the higher the specific impulse will be. The specific impulse of ODE with stoichiometric H2/air mixture and hydrocarbon/air mixture are calculated by using these equations. The results show that ODE can obtain positive net thrust from Ma8 to Ma15.
关键词	Oblique detonation engine ODE Propulsive performance Specific impulse
DOI	10.1016/j.energy.2024.130519
收录类别	SCI ; EI
语种	英语
WOS记录号	WOS:001173971100001
关键词[WOS]	SHOCK-INDUCED COMBUSTION ; INDUCED SUPERSONIC COMBUSTION ; WAVE
WOS研究方向	Thermodynamics ; Energy & Fuels
WOS类目	Thermodynamics ; Energy & Fuels
资助项目	National Natural Science Foundation of China[11672312]
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	Liu, Yunfeng
引用统计
文献类型	期刊论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/94614
专题	高温气体动力学国家重点实验室
作者单位	1.Chinese Acad Sci, Inst Mech, Beijing 100190, Peoples R China; 2.Xiamen Univ, Sch Aerosp Engn, Xiamen 361102, Peoples R China; 3.Hong Kong Polytech Univ, Dept Aeronaut & Aviat Engn, Hong Kong 999077, Peoples R China
推荐引用方式 GB/T 7714	Liu YF,Han, Xin,Zhang, Zijian. Study on the propulsive performance of oblique detonation engine[J]. ENERGY,2024,292:11.
APA	刘云峰,Han, Xin,&Zhang, Zijian.(2024).Study on the propulsive performance of oblique detonation engine.ENERGY,292,11.
MLA	刘云峰,et al."Study on the propulsive performance of oblique detonation engine".ENERGY 292(2024):11.