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NACA-RM-A51H10 REV A
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 4 triangular wing and an all-movable horizontal tail - longitudinal characteristics
Year: 1951
Abstract: INTRODUCTION
The results of tests of an aspect ratio 4 triangular wing (reference 1) have shown the wing to be suitable for use at supersonic speeds. In order to determine the aerodynamic charact8ristics of a similar wing at large scale and low Speed, an investigation has been conducted in the Ames 40-by 80-foot wind tunnel.
The results of reference 1 with regard to aerodynamic-center shift and of reference 2 with regard to damping in pitch indicate that prime consideration should be placed on the use of the wing in an airplane configuration with a horizontal tail. Therefore tests were conducted to determine the low-speed longitudinal characteristics of an airplane configuration with the aspect ratio 4 triangular wing and a horizontal tail. The results of tests reported in reference 3 shoed that the vertical position of a horizontal tail had a marked effect on the longitudinal stability of a model with an aspect ratio 2 wing; hence the vertical position of the tail was varied in the present case. In additional, the effect of a variation of tail span on the longitudinal stability was investigated.
The results of tests of an aspect ratio 4 triangular wing (reference 1) have shown the wing to be suitable for use at supersonic speeds. In order to determine the aerodynamic charact8ristics of a similar wing at large scale and low Speed, an investigation has been conducted in the Ames 40-by 80-foot wind tunnel.
The results of reference 1 with regard to aerodynamic-center shift and of reference 2 with regard to damping in pitch indicate that prime consideration should be placed on the use of the wing in an airplane configuration with a horizontal tail. Therefore tests were conducted to determine the low-speed longitudinal characteristics of an airplane configuration with the aspect ratio 4 triangular wing and a horizontal tail. The results of tests reported in reference 3 shoed that the vertical position of a horizontal tail had a marked effect on the longitudinal stability of a model with an aspect ratio 2 wing; hence the vertical position of the tail was varied in the present case. In additional, the effect of a variation of tail span on the longitudinal stability was investigated.
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NACA-RM-A51H10 REV A
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:39:12Z | |
| date available | 2017-09-04T16:39:12Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | VKMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/102850 | |
| description abstract | INTRODUCTION The results of tests of an aspect ratio 4 triangular wing (reference 1) have shown the wing to be suitable for use at supersonic speeds. In order to determine the aerodynamic charact8ristics of a similar wing at large scale and low Speed, an investigation has been conducted in the Ames 40-by 80-foot wind tunnel. The results of reference 1 with regard to aerodynamic-center shift and of reference 2 with regard to damping in pitch indicate that prime consideration should be placed on the use of the wing in an airplane configuration with a horizontal tail. Therefore tests were conducted to determine the low-speed longitudinal characteristics of an airplane configuration with the aspect ratio 4 triangular wing and a horizontal tail. The results of tests reported in reference 3 shoed that the vertical position of a horizontal tail had a marked effect on the longitudinal stability of a model with an aspect ratio 2 wing; hence the vertical position of the tail was varied in the present case. In additional, the effect of a variation of tail span on the longitudinal stability was investigated. | |
| language | English | |
| title | NACA-RM-A51H10 REV A | num |
| title | Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 4 triangular wing and an all-movable horizontal tail - longitudinal characteristics | en |
| type | standard | |
| page | 29 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext |