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NACA-RM-A7K03
Low-speed investigation of a small triangular wing of aspect ratio 2.0 I : the effect of combination with a body revolution and height above a ground plane
Year: 1948
Abstract: INTRODUCTION
The possible advantages of thin, low-aspect-ratio, triangular wings at supersonic speeds have been shown theoretically by several investigators (references 1,2, and 3). The characteristics of these wings at subsonic and transonic speeds are not so amendable to theoretical treatment, nor have they been extensively investigated experimentally at any speed.
An experimental investigation has been undertaken at the Ames Aeronautical Laboratory of the characteristic of thin, low-aspect-ratio, triangular wings over a wide range of Mach and Reynolds number. For this investigation a triangular wing with an aspect ratio of 2.0, the leading edge swept back 63.4°, of 5 percent of the chord at 20 percent of the chord was selected. The experimental results obtained with this wing from tests at low speed and large scale, have been presented in reference 4.
This report presents the results of test in the Ames 7-by 10-foot wind tunnel to determine the characteristics of the wing alone and in combination with a body of fineness ratio 12.5 Results are also presented for the wing at several heights above a ground plane.
The possible advantages of thin, low-aspect-ratio, triangular wings at supersonic speeds have been shown theoretically by several investigators (references 1,2, and 3). The characteristics of these wings at subsonic and transonic speeds are not so amendable to theoretical treatment, nor have they been extensively investigated experimentally at any speed.
An experimental investigation has been undertaken at the Ames Aeronautical Laboratory of the characteristic of thin, low-aspect-ratio, triangular wings over a wide range of Mach and Reynolds number. For this investigation a triangular wing with an aspect ratio of 2.0, the leading edge swept back 63.4°, of 5 percent of the chord at 20 percent of the chord was selected. The experimental results obtained with this wing from tests at low speed and large scale, have been presented in reference 4.
This report presents the results of test in the Ames 7-by 10-foot wind tunnel to determine the characteristics of the wing alone and in combination with a body of fineness ratio 12.5 Results are also presented for the wing at several heights above a ground plane.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:37:44Z | |
| date available | 2017-09-04T18:37:44Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | JOCTUDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;query=authoCA5893FD081D49A96159DD6EFDEC014A/handle/yse/219563 | |
| description abstract | INTRODUCTION The possible advantages of thin, low-aspect-ratio, triangular wings at supersonic speeds have been shown theoretically by several investigators (references 1,2, and 3). The characteristics of these wings at subsonic and transonic speeds are not so amendable to theoretical treatment, nor have they been extensively investigated experimentally at any speed. An experimental investigation has been undertaken at the Ames Aeronautical Laboratory of the characteristic of thin, low-aspect-ratio, triangular wings over a wide range of Mach and Reynolds number. For this investigation a triangular wing with an aspect ratio of 2.0, the leading edge swept back 63.4°, of 5 percent of the chord at 20 percent of the chord was selected. The experimental results obtained with this wing from tests at low speed and large scale, have been presented in reference 4. This report presents the results of test in the Ames 7-by 10-foot wind tunnel to determine the characteristics of the wing alone and in combination with a body of fineness ratio 12.5 Results are also presented for the wing at several heights above a ground plane. | |
| language | English | |
| title | NACA-RM-A7K03 | num |
| title | Low-speed investigation of a small triangular wing of aspect ratio 2.0 I : the effect of combination with a body revolution and height above a ground plane | en |
| type | standard | |
| page | 43 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext |