IMECH-IR  > 高温气体动力学国家重点实验室
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]. USA:American Institute of Aeronautics and Astronautics Inc, AIAA,2017.
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