Conceptual design and aerodynamic evaluation of hypersonic airplane with double flanking air inlets

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

	Conceptual design and aerodynamic evaluation of hypersonic airplane with double flanking air inlets
	Cui K(崔凯); Hu SC(胡守超); Li GL(李广利); Qu ZP(屈志朋); Situ M
刊名	SCIENCE CHINA-TECHNOLOGICAL SCIENCES
	2013-08
通讯作者邮箱	kcui@imech.ac.cn
卷号	56 期号:8 页码:1980-1988
关键词	hypersonic flanking air inlet waverider computational fluid dynamics(CFD)
ISSN号	1674-7321
通讯作者	Cui, K (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China.
产权排序	[Cui Kai; Hu ShouChao; Li GuangLi; Qu ZhiPeng] Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China; [Situ Ming] 31th Res Inst CASIC, Beijing 100074, Peoples R China
合作状况	国内
中文摘要	To aim at design requirements of high lift-to-drag ratio as well as high volumetric efficiency of next generation hypersonic airplanes, a body-wing-blending configuration with double flanking air inlets layout is presented. Moreover, a novel forebody design methodology which by rotating and assembling two waverider-based surfaces is firstly introduced in this paper. Some typical configurations are designed and their aerodynamic performances are evaluated by computational fluid dynamics. The results for forebodies analysis show that large volumetric efficiency, high lift-to-drag ratio, and uniformly distributed flowfield at the inlet cross section can be assured simultaneously. Furthermore, results of numerical simulation of four integrated configurations with various leading edge shapes, including three power-law curves and a cosine curve clearly show the advantage of high lift-to-drag ratio. Besides, the high pressure generated by the side wall of the airframe can be partly captured by the reasonably designed wings in the condition of small flight attack angle. Then the order of lift-to-drag ratio of four configurations at 0 degree flight attack angle is completely different from the condition of 4-degree flight attack angle. This result demonstrates that the curve shape of the leading edge is very important for the lift-to-drag ratio of the aircraft, and it should be further optimized under the cruising attack angle in future work.
学科主题	计算流体力学
分类号	二类/Q2
收录类别	SCI ; EI
资助信息	National Natural Science Foundation of China [90916013]
原文出处	http://dx.doi.org/10.1007/s11431-013-5288-0
语种	英语
WOS记录号	WOS:000322525800018
公开日期	2013-09-27
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/47448]
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	Cui K,Hu SC,Li GL,et al. Conceptual design and aerodynamic evaluation of hypersonic airplane with double flanking air inlets[J]. SCIENCE CHINA-TECHNOLOGICAL SCIENCES,2013,56(8):1980-1988.
APA	崔凯,胡守超,李广利,屈志朋,&Situ M.(2013).Conceptual design and aerodynamic evaluation of hypersonic airplane with double flanking air inlets.SCIENCE CHINA-TECHNOLOGICAL SCIENCES,56(8),1980-1988.
MLA	崔凯,et al."Conceptual design and aerodynamic evaluation of hypersonic airplane with double flanking air inlets".SCIENCE CHINA-TECHNOLOGICAL SCIENCES 56.8(2013):1980-1988.