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Experimental investigation of the pressures, heat transfer, and surface flow patterns around a blunt half-cone lifting reentry body at a Mach number of 9.6

机译：以马赫数9.6计算的钝半圆锥提升再入体周围的压力，传热和表面流动模式的实验研究

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作者
Coe, F. S., III; Feller, W. V.;
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年度 1961
页码 1-61
总页数 61
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
BLUNT BODIES; HEAT TRANSFER; NOSE CONES; REENTRY VEHICLES; SURFACE PROPERTIES;

机译：BLUNT BODIEs;传播热量;鼻子锥; REENTRY车辆;表面特性;

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1. Experimental investigation of heat transfer over double disk spike-blunt body at Mach 5.7 [J] . Narayana Gopalakrishna, Selvaraj Saravanan Experimental Thermal and Fluid Science: International Journal of Experimental Heat Transfer, Thermodynamics, and Fluid Mechanics . 2019,第期

机译：马赫5.7马蹄铁溅物体传热试验研究
2. Heat transfer reduction using combination of spike and counterflow jet on blunt body at high Mach number flow [J] . Eghlima Z., Mansour K., Fardipour K. Acta astronautica . 2018,第FEBa期

机译：在高马赫数流量下，通过在钝体上使用尖峰和逆流喷射相结合来减少传热
3. NH_3 condensation in a plate heat exchanger: Experimental investigation on flow patterns, heat transfer and frictional pressure drop [J] . Xuan Tao, Elias Dahlgren, Maaike Leichsenring, International Journal of Heat and Mass Transfer . 2020,第Apra期

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4. Study of Catalytic Effects at Reentry Vehicle. MHD Heat Flux Mitigation In Irradiative Hypersonic Flow Around A Blunt Body With Ablating Carbon Surface [C] . V.A. Bityurin, A.N. Bocharov AIAA SciTech forum;Aerospace sciences meeting . 2014

机译：再入车辆催化作用的研究。碳表面消融的钝体周围辐射高超音速流中的MHD热通量缓解
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 on convective heat transfer and pressure drop of cone helically coiled tube heat exchanger using carbon nanotubes/water nanofluids [O] . K. Palanisamy, P.C. Mukesh Kumar 2019

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7. An experimental investigation of heat transfer rates on a blunt body in hypersonic flow [O] . Richards Homer K. 1957

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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 pressures, heat transfer, and surface flow patterns around a blunt half-cone lifting reentry body at a Mach number of 9.6

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