Effects of nose shape, afterbody shape, fineness ratio, and transition strips are presented at several subsonic Mach numbers through angle of attack range from -- 4 to 24°; applicability to recoverable low lift vehicles capable of atmospheric entry at high speeds.
Some effects of nose bluntness and fineness ratio on static longitudinal aerodynamic characteristics of bodies of revolution at subsonic speeds
NASA -- Tech Note
1961
65 pages
Report
Englisch
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