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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

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

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作者
Jones, R. A.;
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年度 1963
页码 1-49
总页数 49
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
APOLLO SPACECRAFT; FLOW DISTRIBUTION; HEAT TRANSFER; PRESSURE DISTRIBUTION; AFTERBODIES; GRAPHS (CHARTS); REYNOLDS NUMBER; STATIC PRESSURE;

机译：apOLLO spaCECRaFT;流量分配;传播热量;压力分布; aFTERBODIEs;图表（图表）; REYNOLDs NUmBER;静压力;

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8. Experimental heat transfer distributions over launch and entry configuration of an 0.45 scale Apollo model /H-2/ at Mach numbers of 8 and 10. Appendix A - Plotted heat transfer distributions tunnel B, volume 2 [R] . 1962

机译：0.45比例apollo模型/ H-2 /的发射和进入配置的实验传热分布，马赫数为8和10.附录a - 绘制的传热分布隧道B，第2卷

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

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