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NACA-TN-3671
Wind-tunnel investigation of the effect of clipping the tips of triangular wings of different thickness, camber, and aspect ratio - transonic bump method
Year: 1956
Abstract: The investigation reported herein was conducted on a transonic bump to determine the aerodynamic characteristics of a series of triangular wings. Four basic triangular-wing plan forms having aspect ratios of 2.0, 2.5, 3.0, and 4.0 were tested. The tips of these wings were progressively clipped to provide taper ratios of 0.1, 0.2, 0.3, 0.4, and in some cases 0.5. The NACA 63A00X profile was used with thickness-to-chord ratios of 0.02, 0.04, and 0.06. Wings having the NACA 63A(1.5)04 section were also investigated for each aspect ratio. Data were obtained over a Mach number range from 0.60 to 1.10 corresponding to a test Reynolds number range from 1.85 million to 2.90 million. Lift, drag, and pitching-moment coefficients are presented for each of the wings investigated.
In general, the greatest decrease in drag-rise factor appeared with the change in taper ratio from 0 to 0.1.
In general, the greatest decrease in drag-rise factor appeared with the change in taper ratio from 0 to 0.1.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:16:43Z | |
| date available | 2017-09-04T17:16:43Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | ZGOUYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/140147 | |
| description abstract | The investigation reported herein was conducted on a transonic bump to determine the aerodynamic characteristics of a series of triangular wings. Four basic triangular-wing plan forms having aspect ratios of 2.0, 2.5, 3.0, and 4.0 were tested. The tips of these wings were progressively clipped to provide taper ratios of 0.1, 0.2, 0.3, 0.4, and in some cases 0.5. The NACA 63A00X profile was used with thickness-to-chord ratios of 0.02, 0.04, and 0.06. Wings having the NACA 63A(1.5)04 section were also investigated for each aspect ratio. Data were obtained over a Mach number range from 0.60 to 1.10 corresponding to a test Reynolds number range from 1.85 million to 2.90 million. Lift, drag, and pitching-moment coefficients are presented for each of the wings investigated. In general, the greatest decrease in drag-rise factor appeared with the change in taper ratio from 0 to 0.1. | |
| language | English | |
| title | NACA-TN-3671 | num |
| title | Wind-tunnel investigation of the effect of clipping the tips of triangular wings of different thickness, camber, and aspect ratio - transonic bump method | en |
| type | standard | |
| page | 186 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext |