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NACA-RM-A52K13
Tests in the Ames 40- by 80-foot wind tunnel of an airplane model with an aspect ratio 4 triangular wing and an all-movable horizontal tail - high-lift devices and lateral controls
Year: 1953
Abstract: INTRODUCTION
The low-speed aerodynamic characteristics of an airplane model with an aspect ratio 4 triangular wing and an all-movable horizontal tail have been under investigation in the Ames 40- by 80-foot wind tunnel. The longitudinal aerodynamic characteristics of the model at zero sideslip have been reported in reference 1; included therein were data covering the effect of horizontal-tail aspect ratio and vertical location. The results of the tests of reference I indicated that the horizontal tail having the greater aspect ratio (4.4) located in the extended wing-chord plane gave the best stability and the lowest drag; therefore, this tail configuration was used in the present investigation.
Presented herein are the results of tests of the model with high-lift devices, and lateral and directional controls. The high-lift devices included slotted inboard flaps and plain outboard flaps. Three lateral controls were tested; namely, the inboard flaps, the outboard flaps, and the all-movable horizontal tail. In addition, a rudder of constant chord was tested as a directional control device. The data herein are presented without analysis to expedite publication.
The low-speed aerodynamic characteristics of an airplane model with an aspect ratio 4 triangular wing and an all-movable horizontal tail have been under investigation in the Ames 40- by 80-foot wind tunnel. The longitudinal aerodynamic characteristics of the model at zero sideslip have been reported in reference 1; included therein were data covering the effect of horizontal-tail aspect ratio and vertical location. The results of the tests of reference I indicated that the horizontal tail having the greater aspect ratio (4.4) located in the extended wing-chord plane gave the best stability and the lowest drag; therefore, this tail configuration was used in the present investigation.
Presented herein are the results of tests of the model with high-lift devices, and lateral and directional controls. The high-lift devices included slotted inboard flaps and plain outboard flaps. Three lateral controls were tested; namely, the inboard flaps, the outboard flaps, and the all-movable horizontal tail. In addition, a rudder of constant chord was tested as a directional control device. The data herein are presented without analysis to expedite publication.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:57:36Z | |
| date available | 2017-09-04T15:57:36Z | |
| date copyright | 01/01/1953 | |
| date issued | 1953 | |
| identifier other | BFMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/60902 | |
| description abstract | INTRODUCTION The low-speed aerodynamic characteristics of an airplane model with an aspect ratio 4 triangular wing and an all-movable horizontal tail have been under investigation in the Ames 40- by 80-foot wind tunnel. The longitudinal aerodynamic characteristics of the model at zero sideslip have been reported in reference 1; included therein were data covering the effect of horizontal-tail aspect ratio and vertical location. The results of the tests of reference I indicated that the horizontal tail having the greater aspect ratio (4.4) located in the extended wing-chord plane gave the best stability and the lowest drag; therefore, this tail configuration was used in the present investigation. Presented herein are the results of tests of the model with high-lift devices, and lateral and directional controls. The high-lift devices included slotted inboard flaps and plain outboard flaps. Three lateral controls were tested; namely, the inboard flaps, the outboard flaps, and the all-movable horizontal tail. In addition, a rudder of constant chord was tested as a directional control device. The data herein are presented without analysis to expedite publication. | |
| language | English | |
| title | NACA-RM-A52K13 | num |
| title | Tests in the Ames 40- by 80-foot wind tunnel of an airplane model with an aspect ratio 4 triangular wing and an all-movable horizontal tail - high-lift devices and lateral controls | en |
| type | standard | |
| page | 46 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1953 | |
| contenttype | fulltext |