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NACA-RM-A51L03
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail : lateral characteristics
Year: 1952
Abstract: INTRODUCTION
A study of the low-speed characteristics of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail has been undertaken in the Ames 40- by 80-foot wind tunnel. The results of tests to determine the longitudinal characteristics, reported in reference 1, showed that of the three vertical positions of the horizontal tail used, namely, 0-, 25-, and 50-percent wing semispan above the wing-chord plane, only the lowest provided satisfactory longitudinal stability. Accordingly, this position of the horizontal tail was selected for the investigation of the low-speed aerodynamic characteristics of the airplane configuration in sideslip. The investigation also included tests of the wing alone, wing-fuselage, and wing-fuselage-vertical-tail combinations. The results are presented herein without analysis in order to expedite publication.
A study of the low-speed characteristics of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail has been undertaken in the Ames 40- by 80-foot wind tunnel. The results of tests to determine the longitudinal characteristics, reported in reference 1, showed that of the three vertical positions of the horizontal tail used, namely, 0-, 25-, and 50-percent wing semispan above the wing-chord plane, only the lowest provided satisfactory longitudinal stability. Accordingly, this position of the horizontal tail was selected for the investigation of the low-speed aerodynamic characteristics of the airplane configuration in sideslip. The investigation also included tests of the wing alone, wing-fuselage, and wing-fuselage-vertical-tail combinations. The results are presented herein without analysis in order to expedite publication.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:14:50Z | |
| date available | 2017-09-04T15:14:50Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | MEMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/13697 | |
| description abstract | INTRODUCTION A study of the low-speed characteristics of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail has been undertaken in the Ames 40- by 80-foot wind tunnel. The results of tests to determine the longitudinal characteristics, reported in reference 1, showed that of the three vertical positions of the horizontal tail used, namely, 0-, 25-, and 50-percent wing semispan above the wing-chord plane, only the lowest provided satisfactory longitudinal stability. Accordingly, this position of the horizontal tail was selected for the investigation of the low-speed aerodynamic characteristics of the airplane configuration in sideslip. The investigation also included tests of the wing alone, wing-fuselage, and wing-fuselage-vertical-tail combinations. The results are presented herein without analysis in order to expedite publication. | |
| language | English | |
| title | NACA-RM-A51L03 | num |
| title | Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail : lateral characteristics | en |
| type | standard | |
| page | 40 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |