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Aerodynamic Testing at Duplicating Hypersonic Flight Conditions with Hyper-Dragon
Jiang ZL(姜宗林); Yu HR(俞鸿儒)
Source Publication31st International Symposium on Shock Waves 1
2019-03-22
Pages1-10
Conference Name31st International Symposium on Shock Waves
Conference Date2017-07-9~14
Conference PlaceNagoya, Japan
AbstractIn this paper, aerodynamic testing carried out with the JF12 hypervelocity shock tunnel is reported, and three experiments are discussed. The first experiment is aerodynamic heat test in hypersonic boundary layer, and a new thermal sensor for heat flux measurement at the extreme high-temperature condition is described, and the hypersonic boundary physics is explored. The second one is the aerodynamic force testing, and a new concept is proposed for optimizing the force and moment measurement system in shock tunnels. With this technology, the real gas effect is investigated, and its dominating mechanism is considered to be the gas molecular vibration. The last is the scramjet test from which two engine operation models are observed, that is, the continuous and pulsed combustion. Because most of the scramjet tests were conducted in combustion-based test facilities, the experimental data at the duplicated hypersonic flight condition would be of fundamental importance for exploring coupling of combustion, supersonic flow, and shock dynamics.
ISBN978-3-319-91017-8
Language英语
Document Type会议论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/80806
Collection高温气体动力学国家重点实验室
Recommended Citation
GB/T 7714
Jiang ZL,Yu HR. Aerodynamic Testing at Duplicating Hypersonic Flight Conditions with Hyper-Dragon[C]31st International Symposium on Shock Waves 1,2019:1-10.
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