Performance of a detonation driven shock tunnel

	Performance of a detonation driven shock tunnel
	Li JW; Wang Q(汪球); Zhao W(赵伟); Lu P ; Tan YX
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	Because of the high costs of flight tests, ground test facilities are a necessity in hypersonic flow research. Compared with other impulse facilities, shock tunnels show their advantages in relatively large-size models and low operational costs. To continuously improve the capacities of shock tunnels, a new detonation-driven shock tunnel was developed in the Laboratory of High Temperature Gas Dynamics (LHD), Institute of Mechanics, Chinese Academy of Sciences. In this paper, performance of the detonation-driven shock tube is investigated, with the help of numerical calculation. Some key issues, including the filling of the gases, pressure loss caused by diaphragm rupture, and the nearly tailored status are discussed in detail. 漏 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
关键词	Detonation Gas Dynamics Hypersonic Flow Shock Tubes Supersonic Aerodynamics
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/311007/72191
专题	高温气体动力学国家重点实验室
作者单位	1. School of Chemical and Environmental Engineering, North University of China, No.3 XueYuan road, Taiyuan 2.051, China (2) State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, No.15 Beisihuanxi Road, Beijing 3.100190, China
推荐引用方式 GB/T 7714	Li JW,Wang Q,Zhao W,et al. Performance of a detonation driven shock tunnel[C]21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017,2017.

条目包含的文件		下载所有文件
文件名称/大小	文献类型	版本类型	开放类型	使用许可
Cp-2017-036.pdf（468KB）	会议论文		开放获取	CC BY-NC-SA	浏览下载