| Pressure and Heat Flux Calibration of the Long-test-duration Hypervelocity Detonation-driven Shock Tunnel | |
Wang Q(汪球) ; Li JW; Lu P; Li JP(李进平); Zhao W(赵伟); Jiang ZL(姜宗林)
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| Source Publication | 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017 |
| 2017 | |
| Conference Name | 21st AIAA International Space Planes and Hypersonics Technologies Conference |
| Conference Date | 6-9 March 2017 |
| Conference Place | Xiamen, China |
| Abstract | A large detonation-driven shock tunnel, named JF12, was developed for exploring hypersonic physics in Institute of Mechanics, Chinese Academy of Sciences. The shock tunnel is capable of duplicating the flight conditions and conducting full-scale or near full-scale model tests, which can make it easy for extrapolation of experimental data to flight. However, in view of the need for high-quality aerothermodynamic measurements in hypersonic shock tunnels, a detailed evaluation of the flowfield uniformity and standard model tests are necessary. In this paper, calibration of the Mach 8 nozzle was first presented. Pitot pressure and stagnation heat transfer data acquired using a Pitot rake were discussed to analyze the nozzle flow uniformity. Besides, a precision built 7-deg sharp cone instrumented with heat gages was used. Corresponding numerical simulations were also conducted for comparison. Results showed that good uniformity was found and a core flow region of approximately 1.8 to 2 m diameter was observed. And heat transfer measurement uncertainty was within 卤10%, which was quite good in hypersonic shock tunnels currently. 漏 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. |
| Keyword | Calibration Detonation Heat Transfer Nozzles Spacecraft Supersonic Aerodynamics Thermodynamics Uncertainty Analysis |
| ISBN | 978-1-62410-463-3 |
| URL | 查看原文 |
| Indexed By | EI |
| Language | 英语 |
| Document Type | 会议论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/72193 |
| Collection | 高温气体动力学国家重点实验室 |
| Affiliation | 1. State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, No.15 Beisihuanxi Road, Beijing 2.100190, China |
| Recommended Citation GB/T 7714 | Wang Q,Li JW,Lu P,et al. Pressure and Heat Flux Calibration of the Long-test-duration Hypervelocity Detonation-driven Shock Tunnel[C]21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017,2017. |
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| File Name/Size | DocType | Version | Access | License | ||
| Cp-2017-038.pdf（679KB） | 会议论文 | 开放获取 | CC BY-NC-SA | View Download | ||
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