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APOLLO Afterbody Heat Transfer and Pressure with and Without Ablation at M Infinity of 5.8 to 8.3

机译：apOLLO后体传热和压力有无消融，m无穷大为5.8至8.3

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作者
Lee, G.; Sundell, R. E.;
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年度 1966
页码 1-4
总页数 4
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
Ablation ; Afterbody ; Apollo spacecraft ; Heat transfer ; Cone ; Enthalpy ; Mach number ; Measurement ; Model ; Nose ; Pressure ; Reynolds number ; Spacecraft ; Stream;

机译：消融;后体;阿波罗宇宙飞船;传热;锥;焓;马赫数;测量;模型;鼻子;压力;雷诺数;航天器;流;
入库时间 2022-08-29 11:17:26

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专利

1. Analysis of Apollo Command Module Afterbody Heating Part Ⅰ: AS-202 [J] . Michael J. Wright, Dinesh K. Prabhu, Edward R. Martinez Journal of Thermophysics and Heat Transfer . 2006,第1期

机译：阿波罗指令模块车身后加热分析：第一部分：AS-202
2. Reduced order models for heat flux and pressure distributions on space debris afterbodies [J] . Drouet Vincent, Prevereaud Ysolde, Moschetta Jean-Marc, Acta astronautica . 2021,第Apra期

机译：减少热通量和压力分布的订单模型
3. Convective heat transfer at high subcritical pressures in tubes with and without flow obstacles [J] . Eter Ahmad, Groeneveld De, Tavoularis Stavros Nuclear Engineering and Design . 2017,第Jula期

机译：带有和不带有流动障碍的管子在高亚临界压力下的对流传热
4. Simulations of Afterbody Heating Rates on the Apollo Command Module for AS- 202 Using Hyperbolic Grids [C] . C. Tang AIAA Fluid Dynamics Conference . 2006

机译：使用双曲线网格在AS-202的Apollo命令模块上模拟后车身加热速率
5. Heat transfer and pressure drop of refrigerant R404A at near-critical and supercritical pressures. [D] . Jiang, Yirong. 2004

机译：制冷剂R404A在近临界和超临界压力下的传热和压降。
6. Endogenous Heat‐Shock Protein Induction with or Without Radiofrequency Ablation or Cryoablation in Patients with Stage IV Melanoma [O] . Evidio Domingo‐Musibay, *, James M. Heun, 2017

机译：IV期黑色素瘤患者内源性热休克蛋白诱导（伴或不伴射频消融或冷冻消融）
7. PM-1 task 5, subtask 5.8 local boiling heat transfer tests : single tube heat transfer and pressure drop tests / [O] . Frank, S., Norin, M., Jicha, J., 1961

机译：pm-1任务5，子任务5.8局部沸腾传热试验：单管传热和压降试验/
8. Apollo afterbody heat transfer and pressure with and without ablation at M infinity of 5.8 to 8.3 [R] . Lee, G., Sundell, R. E. 1966

机译：apollo后体传热和压力有无消融，m无穷大为5.8至8.3

APOLLO Afterbody Heat Transfer and Pressure with and Without Ablation at M Infinity of 5.8 to 8.3

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