| Performance of a detonation driven shock tunnel |
| Li JW ; Wang Q(汪球); Zhao W(赵伟); Lu P; Tan YX
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| Source Publication | 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
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| 2017
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| Conference Name | 21st AIAA International Space Planes and Hypersonics Technologies Conference
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| Conference Date | 6-9 March 2017
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| Conference Place | Xiamen, China
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| Abstract | 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. |
| Keyword | Detonation
Gas Dynamics
Hypersonic Flow
Shock Tubes
Supersonic Aerodynamics
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| ISBN | 978-1-62410-463-3
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| URL | 查看原文
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| Indexed By | EI
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| Language | 英语
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| Document Type | 会议论文
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| Identifier | http://dspace.imech.ac.cn/handle/311007/72191
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| Collection | 高温气体动力学国家重点实验室
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| Affiliation | 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
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Recommended Citation
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.
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