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Numerical Investigation of the Influence of Fuselage Corner Bluntness on a High-Pressure Capturing Wing Configuration

文献类型：期刊论文

作者Xi XZ(席小喆)2,3; Li GL(李广利)2,3; Wang HX(王浩祥)1; Xiao, Yao2,3; Chang SY(常思源)3; Cui K(崔凯)2,3
刊名JOURNAL OF AEROSPACE ENGINEERING
出版日期2025-03-01
卷号38期号:2页码:13
关键词High-pressure capturing wing (HCW) Flow separation Numerical simulation Fuselage corner bluntness Aerodynamic performance
ISSN号0893-1321
DOI10.1061/JAEEEZ.ASENG-5160
通讯作者Li, Guangli(liguangli@imech.ac.cn)
英文摘要Under beneficial aerodynamic interference, the innovative high-pressure capturing wing (HCW) configuration exhibits remarkable aerodynamic performance at hypersonic speeds. At the same time, the additional lifting surface of the HCW may significantly improve the lift at subsonic speeds, which makes the configuration a promising concept for air vehicle design covering a wide speed range. Recent research has shown that the HCW can generate flow separations on the upper surface of the fuselage in certain subsonic flow conditions, which considerably deteriorates aerodynamic performance of the air vehicle. In this paper, a hybrid configuration combining HCW with a cone-truncated cone fuselage is studied. Numerical simulations are conducted to examine the impact of fuselage corner bluntness on flow characteristics and aerodynamic performances in typical subsonic (Mach 0.7) and hypersonic (Mach 7) flow conditions. The results show that at Mach 0.7, with the increase of blunt radius at the fuselage corner, the flow separations on the upper surface of the fuselage can be effectively restrained. The lift coefficient of the vehicle remains virtually unchanged, while the drag coefficient decreases significantly by 69% when the blunt radius is 600 mm. At Mach 7, the fuselage corner bluntness leads to a slight drop of 9% and 8% in the lift and drag coefficient of the vehicle, respectively, while the lift-to-drag ratio remains virtually unchanged.
分类号二类
WOS关键词DESIGN
资助项目National Natural Science Foundation of China[12002347] ; Chinese Academy of Sciences Foundation Frontier Scientific Research Program[ZDBS-LY-JS005]
WOS研究方向Engineering
语种英语
WOS记录号WOS:001396445100007
资助机构National Natural Science Foundation of China ; Chinese Academy of Sciences Foundation Frontier Scientific Research Program
其他责任者Li, Guangli
源URL[http://dspace.imech.ac.cn/handle/311007/98189]  
专题力学研究所_高温气体动力学国家重点实验室
作者单位1.Fourth Acad Aerosp Sci & Ind, Dept 4, Beijing 102308, Peoples R China
2.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100190, Peoples R China;
3.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China;
推荐引用方式
GB/T 7714		 Xi XZ,Li GL,Wang HX,et al. Numerical Investigation of the Influence of Fuselage Corner Bluntness on a High-Pressure Capturing Wing Configuration[J]. JOURNAL OF AEROSPACE ENGINEERING,2025,38(2):13.
APA 席小喆,李广利,王浩祥,Xiao, Yao,常思源,&崔凯.(2025).Numerical Investigation of the Influence of Fuselage Corner Bluntness on a High-Pressure Capturing Wing Configuration.JOURNAL OF AEROSPACE ENGINEERING,38(2),13.
MLA 席小喆,et al."Numerical Investigation of the Influence of Fuselage Corner Bluntness on a High-Pressure Capturing Wing Configuration".JOURNAL OF AEROSPACE ENGINEERING 38.2(2025):13.

入库方式： OAI收割

来源：力学研究所

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