The drag of finite-length cylinders determined from flight tests at high Reynolds numbers for a Mach number range from 0.5 to 1.3 / Clement J. Welsh.
Reults of a free-flight investigation to determine the drg of circular, finite-length cylinders are presented for a Mach number range from about 0.5 to 1.3. Fineness ratios of the cylinders tested were 15, 30, and 60. Results of previous experimental tests of circular cylinders having infinite finen...
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| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
1953.
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
2941. |
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| Summary: | Reults of a free-flight investigation to determine the drg of circular, finite-length cylinders are presented for a Mach number range from about 0.5 to 1.3. Fineness ratios of the cylinders tested were 15, 30, and 60. Results of previous experimental tests of circular cylinders having infinite fineness ratios are included in this paper for comparison. For supersonic speeds, the drag of circular cylinders is largely independent of fineness ratio and Reynolds numbers. At subsonic Mach numbers, the drag of finite-length cylinders (fineness ratios of about 60 and below) increases as their fineness ratios increase. |
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| Item Description: | "June 1953." NACA TN Number 2941. |
| Physical Description: | 12 pages : illustrations ; 28 cm. |
| Bibliography: | Includes bibliographical references. |