Experimental investigation of hypersonic flow induced separation over double wedges

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	Experimental investigation of hypersonic flow induced separation over double wedges
	Tokitada Hashimoto
刊名	JOURNAL OF THERMAL SCIENCE
	2009
卷号	18 期号:3 页码:220,225
英文摘要	Flow separation occurs over the compression corners generated by deflected control surfaces on hypersonic re-entry vehicles and in the inlet of scram jet engines. Configurations like a double wedge and double cone model are useful for studying the separated flow features. Flow fields around concave corners are relatively complicated and produce several classical viscous flow features depending on the combination of the first and second wedge or cone half apex angles. Particularly characteristic phenomena are mainly shock/boundary layer, shock/shock interaction, unsteady shear layers and non-linear shock oscillations. Although most of these basic gas dynamics characteristics are well known, it is not clear what happens at high enthalpy conditions. This paper reports a result of flow fields over a double wedge at a stagnation enthalpy of 4.8 MJ/kg. The experiment was carried out in a free piston shock tunnel at a nominal Mach number of 6.99. Schlieren and double exposure holographic interferometry were applied to visualize the flow field over the double wedge.
公开日期	2013-01-09
内容类型	期刊论文
源URL	[http://ir.etp.ac.cn/handle/311046/51807]
专题	工程热物理研究所_Journal of Thermal Science
推荐引用方式 GB/T 7714	Tokitada Hashimoto. Experimental investigation of hypersonic flow induced separation over double wedges[J]. JOURNAL OF THERMAL SCIENCE,2009,18(3):220,225.
APA	Tokitada Hashimoto.(2009).Experimental investigation of hypersonic flow induced separation over double wedges.JOURNAL OF THERMAL SCIENCE,18(3),220,225.
MLA	Tokitada Hashimoto."Experimental investigation of hypersonic flow induced separation over double wedges".JOURNAL OF THERMAL SCIENCE 18.3(2009):220,225.