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NACA-TN-3501
The transonic characteristics of 22 rectangular, symmetrical wing models of varying aspect ratio and thickness
Year: 1955
Abstract: An investigation to determine the aerodynamic characteristics of a series of thin, rectangular wings was conducted in the Ames 16-foot high-speed wind tunnel, utilizing the transonic bump technique over a mach number range from 0.40 to 1.10, corresponding to a Reynolds number range from 1.25 to 2.05 million. The lift, drag, and pitching-moment data are presented for wings having aspect ratios of 6, 4, 3, 2, 1.5, 1, and 0.5, and NACA 63AOXX sections with thickness-to-chord ratios of 10,8,6,4, and 2 percent.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:05:13Z | |
| date available | 2017-09-04T16:05:13Z | |
| date copyright | 01/01/1955 | |
| date issued | 1955 | |
| identifier other | RVNUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/68509 | |
| description abstract | An investigation to determine the aerodynamic characteristics of a series of thin, rectangular wings was conducted in the Ames 16-foot high-speed wind tunnel, utilizing the transonic bump technique over a mach number range from 0.40 to 1.10, corresponding to a Reynolds number range from 1.25 to 2.05 million. The lift, drag, and pitching-moment data are presented for wings having aspect ratios of 6, 4, 3, 2, 1.5, 1, and 0.5, and NACA 63AOXX sections with thickness-to-chord ratios of 10,8,6,4, and 2 percent. | |
| language | English | |
| title | NACA-TN-3501 | num |
| title | The transonic characteristics of 22 rectangular, symmetrical wing models of varying aspect ratio and thickness | en |
| type | standard | |
| page | 110 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1955 | |
| contenttype | fulltext |