Experimental investigation of hypersonic flight-duplicated shock tunnel characteristics

doi:10.1007/s10409-020-01036-0

	Experimental investigation of hypersonic flight-duplicated shock tunnel characteristics
	Yuan CK(苑朝凯)1 ; Jiang ZL(姜宗林)1,2
通讯作者	Jiang, Z. L.(zljiang@imech.ac.cn)
发表期刊	ACTA MECHANICA SINICA
	2021-01-09
页码	12
ISSN	0567-7718
摘要	Hypersonic air-breathing propulsion is one of the key techniques for future aviation and the ground aerodynamic testing for full scale test models with sufficient test time at flight conditions is of fundamental importance for verifying hypersonic air-breathing engines. Based on the backward detonation-driven concept, the hypersonic flight-duplicated shock tunnel (or JF-12 shock tunnel) has been successfully constructed and calibrated. This facility is capable of reproducing airflow for Mach numbers ranging from 5 to 9 at an altitude of 25-50 km, with a test duration of more than 100 ms. To quantify the performance of the shock tunnel, experiments were conducted to investigate the aerodynamic characteristics of the test flows and the effects of several critical techniques that play important roles in the operation of the shock tunnel. The stagnation pressure was constant within +/- 5% and the average stagnation pressure varied by less than 0.048%/ms. The variation of the stagnation pressure in repeated experiments is less than 2.0%, indicating the good repeatability of the wind tunnel. The non-uniformity of the Mach number in the core flow field at the nozzle exit was within +/- 2.5%. Additional, a uniform flow field is established upstream of the nozzle exit. The axial gradients of the flow field are small since the Mach number varies less than 1.7%/m. Findings regarding the ignition technology, diaphragm ruptures, detonation driver capacity, incident shock-wave decay, and tunnel operation mode are also presented. The findings of this study are not only helpful for operating the shock tunnel, but can also assist the future development of hypersonic wind tunnels. Graphic abstract
关键词	Hypersonics Shock tunnels Flow characteristics
DOI	10.1007/s10409-020-01036-0
收录类别	SCI ; EI ; CSCD
语种	英语
WOS记录号	WOS:000606371600002
关键词[WOS]	HIGH-ENTHALPY ; DETONATION ; FLOW
WOS研究方向	Engineering ; Mechanics
WOS类目	Engineering, Mechanical ; Mechanics
资助项目	National Natural Science Foundation of China[11602275] ; National Natural Science Foundation of China[11532014]
项目资助者	National Natural Science Foundation of China
论文分区	二类
力学所作者排名	1
RpAuthor	Jiang, Z. L.
引用统计	被引频次：6[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/311007/85925
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.Univ Chinese Acad Sci, Beijing 100190, Peoples R China
推荐引用方式 GB/T 7714	Yuan CK,Jiang ZL. Experimental investigation of hypersonic flight-duplicated shock tunnel characteristics[J]. ACTA MECHANICA SINICA,2021:12.
APA	苑朝凯,&姜宗林.(2021).Experimental investigation of hypersonic flight-duplicated shock tunnel characteristics.ACTA MECHANICA SINICA,12.
MLA	苑朝凯,et al."Experimental investigation of hypersonic flight-duplicated shock tunnel characteristics".ACTA MECHANICA SINICA (2021):12.

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