Experimental Studies on Model Scramjet in a Mach 6 High Enthalpy Free-Jet Wind Tunnel

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	Experimental Studies on Model Scramjet in a Mach 6 High Enthalpy Free-Jet Wind Tunnel
	Zhang XY(张新宇); Chen LH(陈立红); Gu HB(顾洪斌); Yu G(俞刚); Zhang XY(张新宇)
	2005
会议名称	The 24th International Symposium on Shock Waves
会议日期	2004-07-11
会议地点	Beijing
页码	891-896
通讯作者	张新宇
中文摘要	A side-wall compression scramjet model with different combustor geometries has been tested in a propulsion tunnel that typically provides the testing flow with Mach number of 5.8, total temperature of 1800K, total pressure of 4.5MPa and mass flow rate of 4kg/s. This kerosene-fueled scramjet model consists of a side-wall compression inlet, a combustor and a thrust nozzle. A strut was used to increase the contraction ratio and to inject fuels, as well as a mixing enhancement device. Several wall cavities were also employed for flame-holding. In order to shorten the ignition delay time of the kerosene fuel, a little amount of hydrogen was used as a pilot flame. The pressure along the combustor has an evident raise after ignition occurred. Consequently thrust was observed during the fuel-on period. However, the thrust was still less than the drag of the scramjet model. For this reason, the drag variation produced by different strut and cavities was tested. Typical results showed that the cavities do not influence the drag so much, but the length of the strut does.
收录类别	CPCI-S
会议网址	http://dx.doi.org/10.1007/978-3-540-27009-6_135
会议录	Shock Waves
学科主题	力学
语种	英语
ISBN号	978-3-540-22497-6
WOS记录号	WOS:000231243300135
内容类型	会议论文
源URL	[http://dspace.imech.ac.cn/handle/311007/13771]
专题	力学研究所_力学所知识产出(1956-2008)
通讯作者	Zhang XY(张新宇)
推荐引用方式 GB/T 7714	Zhang XY,Chen LH,Gu HB,et al. Experimental Studies on Model Scramjet in a Mach 6 High Enthalpy Free-Jet Wind Tunnel[C]. 见:The 24th International Symposium on Shock Waves. Beijing. 2004-07-11.http://dx.doi.org/10.1007/978-3-540-27009-6_135.