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NACA-TN-3529
The transonic characteristics of 36 symmetrical wings of varying taper, aspect ratio, and thickness as determined by the transonic-bump technique
Year: 1955
Abstract: An investigation of the effects of plan-form taper on the aerodynamic characteristics of a series of wings having various tapers, aspect ratios, and thicknesses was conducted in the Ames 16-foot high-speed wind tunnel, utilizing the transonic-bump method. The mach number range of the investigation was from 0.6 to 1.1, corresponding to a Reynolds number range of about 1.4 million to 2.0 million. The lift, drag, and pitching-moment data are presented for wings having aspect ratios of 4 (taper ratios of 0.33, 0.5, and 0.72), and NACA 63AOOX sections with thickness-to-chord ratios of 8, 6, 4, and 2 percent.
The results indicate that the greatest effect of taper on the lift curve slope occurred for the wing having the highest aspect ratio and the thinnest section. This effect, which was to increase the lift-curve slope with increasing taper ratio, diminished as the aspect ratio was decreased and/or the thickness increased. Increasing taper ratio generally increased the over-all center-of-pressure travel for all wings in going from subsonic to supersonic speeds.
The results indicate that the greatest effect of taper on the lift curve slope occurred for the wing having the highest aspect ratio and the thinnest section. This effect, which was to increase the lift-curve slope with increasing taper ratio, diminished as the aspect ratio was decreased and/or the thickness increased. Increasing taper ratio generally increased the over-all center-of-pressure travel for all wings in going from subsonic to supersonic speeds.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:02:53Z | |
| date available | 2017-09-04T17:02:53Z | |
| date copyright | 01/01/1955 | |
| date issued | 1955 | |
| identifier other | XVNUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/126429 | |
| description abstract | An investigation of the effects of plan-form taper on the aerodynamic characteristics of a series of wings having various tapers, aspect ratios, and thicknesses was conducted in the Ames 16-foot high-speed wind tunnel, utilizing the transonic-bump method. The mach number range of the investigation was from 0.6 to 1.1, corresponding to a Reynolds number range of about 1.4 million to 2.0 million. The lift, drag, and pitching-moment data are presented for wings having aspect ratios of 4 (taper ratios of 0.33, 0.5, and 0.72), and NACA 63AOOX sections with thickness-to-chord ratios of 8, 6, 4, and 2 percent. The results indicate that the greatest effect of taper on the lift curve slope occurred for the wing having the highest aspect ratio and the thinnest section. This effect, which was to increase the lift-curve slope with increasing taper ratio, diminished as the aspect ratio was decreased and/or the thickness increased. Increasing taper ratio generally increased the over-all center-of-pressure travel for all wings in going from subsonic to supersonic speeds. | |
| language | English | |
| title | NACA-TN-3529 | num |
| title | The transonic characteristics of 36 symmetrical wings of varying taper, aspect ratio, and thickness as determined by the transonic-bump technique | en |
| type | standard | |
| page | 132 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1955 | |
| contenttype | fulltext |