IMECH-IR  > 高温气体动力学国家重点实验室
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)
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
AbstractA 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.
KeywordCalibration Detonation Heat Transfer Nozzles Spacecraft Supersonic Aerodynamics Thermodynamics Uncertainty Analysis
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/311007/72193
Collection高温气体动力学国家重点实验室
Affiliation1. 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]. USA:American Institute of Aeronautics and Astronautics Inc, AIAA,2017.
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