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Experimental investigation of pressure distribution and static aerodynamic characteristics for three supersonic impact ballistic reentry shapes at Mach numbers of 1.93, 2.55, and 3.05

机译：马赫数为1.93,2.55和3.05的三种超音速冲击弹道再入形状的压力分布和静态气动特性的实验研究

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作者
Keith, A. L., Jr.; Morris, O. A.;
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年度 1961
页码 1-42
总页数 42
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
AERODYNAMIC CHARACTERISTICS; REENTRY VEHICLES; SUPERSONIC SPEED; IMPACT TESTS; PRESSURE DISTRIBUTION; WIND TUNNEL STABILITY TESTS;

机译：空气动力学特征; REENTRY车辆;超音速;影响测试;压力分布;风洞稳定性试验;
入库时间 2022-08-29 11:18:55

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机译：基础出口和终端开口对机械编号为1.93,2.55和3.05的排气 - 喷嘴 - 后体组合性能的影响

Experimental investigation of pressure distribution and static aerodynamic characteristics for three supersonic impact ballistic reentry shapes at Mach numbers of 1.93, 2.55, and 3.05

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