Effects of Shock Impingement on Aerothermal and Aerodynamic Performance for High-pressure Capturing Wings

	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)
会议录名称	21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
	2017
会议名称	21st AIAA International Space Planes and Hypersonics Technologies Conference
会议日期	6-9 March 2017
会议地点	Xiamen, China
摘要	The 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.
关键词	Aerodynamics Angle Of Attack Angle Of Attack Indicators Boundary Layers Drag Drag Coefficient High Pressure Effects Hypersonic Aerodynamics Hypersonic Flow Spacecraft
ISBN号	978-1-62410-463-3
URL	查看原文
收录类别	EI
语种	英语
文献类型	会议论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/72185
专题	高温气体动力学国家重点实验室
作者单位	1. 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
推荐引用方式 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]21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017,2017.

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