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
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
AbstractBecause 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.
KeywordDetonation Gas Dynamics Hypersonic Flow Shock Tubes Supersonic Aerodynamics
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/311007/72191
Collection高温气体动力学国家重点实验室
Affiliation1. 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
Recommended Citation
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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