Development of an aerodynamic measurement system for hypersonic rarefied flows.
Development of an aerodynamic measurement system for hypersonic rarefied flows.
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开发高超音速稀薄流气动测量系统。
DOI：
10.1063/1.4905569
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发表时间：
2015
期刊：
影响因子：
--
通讯作者：
Toshiyuki Suzuki
中科院分区：
文献类型：
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作者：
Takashi Ozawa;K. Fujita;Toshiyuki Suzuki
日本宇宙航空研究开发机构近期开发了一座高超声速稀薄风洞（HRWT），以改进对稀薄气体动力学的预测。对高超声速稀薄流的流动特性进行了实验和数值研究。通过使用摆式模型进行动压测量以及皮托管压力测量，我们探究了试验段的流动特性。我们还通过将数值方法与高超声速稀薄风洞测量相结合，增进了对高超声速稀薄流的理解。高超声速稀薄风洞与数值方法之间集成方案的开发，使我们能够估算高超声速稀薄流特性以及直接测量稀薄气体动力学。因此，这座风洞能够产生核心直径为25毫米的气流，其自由流马赫数大于10，克努森数大于0.1。
A hypersonic rarefied wind tunnel (HRWT) has lately been developed at Japan Aerospace Exploration Agency in order to improve the prediction of rarefied aerodynamics. Flow characteristics of hypersonic rarefied flows have been investigated experimentally and numerically. By conducting dynamic pressure measurements with pendulous models and pitot pressure measurements, we have probed flow characteristics in the test section. We have also improved understandings of hypersonic rarefied flows by integrating a numerical approach with the HRWT measurement. The development of the integration scheme between HRWT and numerical approach enables us to estimate the hypersonic rarefied flow characteristics as well as the direct measurement of rarefied aerodynamics. Consequently, this wind tunnel is capable of generating 25 mm-core flows with the free stream Mach number greater than 10 and Knudsen number greater than 0.1.
高超声速稀薄流态下钝体囊姿态稳定性
DOI：
--
发表时间：
2004
期刊：
Journal of Spacecraft and Rockets 41(6)
影响因子：
--
作者：
Fujita;K.;Inatani;Y.;Hiraki;K.
通讯作者：
K.
追踪气球任务中金星进入舱的加热环境
DOI：
--
发表时间：
--
期刊：
Journal of Thermophysics and Heat Transfer (in press)
影响因子：
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作者：
Fujita;K.;Sumi;T.;Yamada;T.;Ishii;N.
通讯作者：
N.