IMECH-IR  > 高温气体动力学国家重点实验室
Modification of hypersonic waveriders by vorticity-based boundary layer displacement thickness determination method
Liu W(刘文); Zhang CA(张陈安); Wang FM(王发民)
Source PublicationAerospace Science and Technology
2018-04
Volume75Pages:200-214
ISSN1270-9638
Abstract

For general hypersonic vehicles flying at high altitudes and Mach numbers, the appearance of the large boundary layer displacement thickness can change the pressure distribution and aerodynamic characteristics significantly. As for the waverider, another side effect is that the shock wave position is deflected downward evidently even at the design Mach number, which is adverse for the shock wave being attached to the leading edge and may lead to more leakage of high pressure gas from the lower surface onto the upper surface. Therefore, this paper first develops a vorticity-based method to determine the boundary layer displacement thickness, in combination with the tangent wedge/cone method. Then, trying to alleviate the high pressure gas leakage near the leading edge, modification of a viscous optimized waverider is conducted under the condition of strong viscous interaction, by deducting the corresponding boundary layer displacement thickness from the original lower surface along the normal direction. Results show that the shock wave position around the lower surface of the modified waverider under the condition of strong viscous interaction is very close to that of the inviscid basic flowfield around the original waverider, which means less leakage of high pressure gas. But it's found that such change has little influence on the aerodynamic characteristics of the upper surface. However, an interesting discovery is that due to the lower pressure near the leading edge of the modified lower surface, the wave drag is lowered for the same lift, thus the lift-to-drag ratio is improved. The modified waverider also exhibits higher lift-to-drag ratio at large angles of attack when compared to waveriders with upper expansion surfaces. Overall, a vorticity-based boundary layer displacement thickness determination method is proposed in this paper, which is then used to modify waveriders to achieve higher aerodynamic efficiency.

DOI10.1016/j.ast.2017.12.020
Indexed BySCI ; EI
Language英语
WOS IDWOS:000429753800016
Classification一类
Ranking2
Citation statistics
Cited Times:1[WOS]   [WOS Record]     [Related Records in WOS]
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/77373
Collection高温气体动力学国家重点实验室
空天飞行科技中心(筹)
Corresponding AuthorZhang CA(张陈安)
Affiliation1.Northwestern Polytechnical University, Xi'an 710072, People's Republic of China
2.Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, People's Republic of China
Recommended Citation
GB/T 7714
Liu W,Zhang CA,Wang FM. Modification of hypersonic waveriders by vorticity-based boundary layer displacement thickness determination method[J]. Aerospace Science and Technology,2018,75:200-214.
APA Liu W,Zhang CA,&Wang FM.(2018).Modification of hypersonic waveriders by vorticity-based boundary layer displacement thickness determination method.Aerospace Science and Technology,75,200-214.
MLA Liu W,et al."Modification of hypersonic waveriders by vorticity-based boundary layer displacement thickness determination method".Aerospace Science and Technology 75(2018):200-214.
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