IMECH-IR  > 高温气体动力学国家重点实验室
Effects of Shock Impingement on Aerothermal and Aerodynamic Performance for High-pressure Capturing Wings
Li GL(李广利); Cui K(崔凯); Xiao Y(肖尧); Xu YZ(徐应洲)
Source Publication21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
2017
Conference Name21st AIAA International Space Planes and Hypersonics Technologies Conference
Conference Date6-9 March 2017
Conference PlaceXiamen, China
AbstractThe high-pressure capturing wing (HCW) is a novel device that can improve the aerodynamic performance for large volume high-speed aircrafts. In hypersonic flows, the sharp leading edge of HCW must be blunted because of the severe aerothermal load. The oblique shock induced by body intersects to the bow shock induced by HCW. This paper proposes three cases based on the shock interaction location and studies the corresponding aerodynamic and aerothermal performance by numerical simulation under Mach 6 and zero angle of attack. The results show that the maximal heat flux and drag coefficient of HCW is determined by the interaction location. When the shock impinges on the inside of HCW, the shock boundary layer interaction occurs which lead to the increase of local heat flux on the lower surface of HCW. However, the maximal heat flux is almost the same with the freestream stagnation-point heat flux. The local extreme heat flux in the lower surface of HCW is about 20 percentage of the freestream stagnation-point heat flux. The drag coefficient is almost the same with freestream drag coefficient. When the shock impinges on the HCW leading edge, the type IV interference appears which could cause high pressure and heat flux on the surface. The non-dimensional maximal heat flux is about 3.5 and the maximal drag coefficient is about 1.8 in this case. When the oblique shock impinges on the outside of HCW, the non-dimensional maximal heat flux is about 1.5 and the drag coefficient is about 2.7. 漏 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
KeywordAerodynamics Angle Of Attack Angle Of Attack Indicators Boundary Layers Drag Drag Coefficient High Pressure Effects Hypersonic Aerodynamics Hypersonic Flow Spacecraft
ISBN978-1-62410-463-3
URL查看原文
Indexed ByEI
Language英语
Document Type会议论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/72185
Collection高温气体动力学国家重点实验室
Affiliation1. LHD of Institute of Mechanics, Chinese Academy of Sciences, Beijing
2.190, China (2) School of Engineering Science, University of Chinese Academy of Sciences, Beijing
3.100049, China
Recommended Citation
GB/T 7714
Li GL,Cui K,Xiao Y,et al. Effects of Shock Impingement on Aerothermal and Aerodynamic Performance for High-pressure Capturing Wings[C]. USA:American Institute of Aeronautics and Astronautics Inc, AIAA,2017.
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