Wind tunnel study made at several fineness ratios between 2 and 14 for range of R from 300,000 to 1,650,000; effects of hemispherical ends on drag characteristics were also obtained; data may be useful in making preliminary calculations on rockets and aircraft having long nose sections at high angles of attack.
Effects of fineness ratio and Reynolds number on low-speed crosswind drag characteristics of circular and modified-square cylinders
NASA -- Tech Note
1960
15 pages
Report
Englisch
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