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Experimental investigation of the flow field and heat transfer over the Apollo-capsule afterbody at a Mach number of 20

机译：马赫数为20的阿波罗胶囊体后流场和传热的实验研究

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作者
Kussoy, M.; Marvin, J. G.;
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年度 1965
页码 1-28
总页数 28
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
APOLLO SPACECRAFT; COMMAND MODULES; FLOW DISTRIBUTION; HYPERSONIC HEAT TRANSFER; WIND TUNNEL MODELS; BOUNDARY LAYER SEPARATION; FLOW VISUALIZATION; HEAT TRANSFER COEFFICIENTS; HYPERVELOCITY WIND TUNNELS; PRESSURE DISTRIBUTION;

机译：apOLLO spaCECRaFT;命令模块;流量分配;超音速换热;风洞模型;边界层分离;流动可视化;换热系数; HYpERVELOCITY WIND TUNNELs;压力分布;

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5. Experimental pressure and heat transfer investigation over a "directed-energy air spike" inlet at flow mach numbers of 10 to 20, stagnation temperature of 1000 K, and arc powers up to 127 KW. [D] . Toro, Paulo Gilberto de Paula. 1998

机译：在流量为10至20的马赫数，停滞温度为1000 K，电弧功率高达127 KW的“定向能空气尖峰”入口上进行实验压力和传热研究。
6. Experimental Investigation of the Flow and Heat Transfer Characteristics in Microchannel Heat Exchangers with Reentrant Cavities [O] . Binghuan Huang, Haiwang Li, Tiantong Xu 2020

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7. Experimental Investigation of a Liquid Metal Flow and Heat Transfer under a Transverse Magnetic Field : 2nd Repors, Heat Transfer for a Rectangular Channel Flow [O] . Kenzo Kitamura, Akira Yasukawa, Masaru Hirai 1980

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8. Experimental investigation of the overall pressure distribution, flow field, and afterbody heat transfer distribution of an Apollo reentry configuration at a Mach number of 8 [R] . Jones, R. A. 1963

机译：阿赫罗再入配置的总压力分布，流场和后体传热分布的实验研究，马赫数为8

Experimental investigation of the flow field and heat transfer over the Apollo-capsule afterbody at a Mach number of 20

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