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NACA-RM-L9F14
Effect of sweepback on the low-speed static and rolling stability derivatives of thin tapered wings of aspect ratio 4
Year: 1949
Abstract: INTRODUCTION
The influence of a number of different geometric parameters on the rolling stability derivatives of wings have been investigated in the Langley stability tunnel by means of the rolling-flow technique. (See reference 1.) The investigations have included the effects of aspect ratio and sweep (reference 2), taper ratio (reference 3), dihedral (reference 4), and airfoil section (reference 5). All of the investigations were performed at low Mach numbers and with moderately thick wings. In order to obtain an indication of the rolling characteristics of sweptback wings at higher Subsonic speeds, a series of thin wings (NACA 65A006 airfoil section) were tested in the Langley high-speed 7- by 10-foot wind tunnel at Mach numbers from about 0.4 to about 0.9. (See reference 6.) Results were obtained over an angle-of-attack range from 0.3° to 6.5° for the damping-in-roll derivative Clp and for the aileron effectiveness.
The results of the investigation reported herein were obtained in the rolling-flow test section of the Langley stability tunnel, and the models were those used for the investigation reported in reference 6. The purpose of the present tests was to obtain more complete information, at least at low speeds, on the static and rolling characteristics of the wings and also to obtain a correlation between techniques of the Langley stability tunnel (rolling flow) and the Langley 7- by 10-foot tunnel (free rotation) for determining the damping in roll.
The wings tested were sweptback 3.6°, 32.6°, and 46.7° and had an aspect ratio of 4 and taper ratio of 0.6.
The influence of a number of different geometric parameters on the rolling stability derivatives of wings have been investigated in the Langley stability tunnel by means of the rolling-flow technique. (See reference 1.) The investigations have included the effects of aspect ratio and sweep (reference 2), taper ratio (reference 3), dihedral (reference 4), and airfoil section (reference 5). All of the investigations were performed at low Mach numbers and with moderately thick wings. In order to obtain an indication of the rolling characteristics of sweptback wings at higher Subsonic speeds, a series of thin wings (NACA 65A006 airfoil section) were tested in the Langley high-speed 7- by 10-foot wind tunnel at Mach numbers from about 0.4 to about 0.9. (See reference 6.) Results were obtained over an angle-of-attack range from 0.3° to 6.5° for the damping-in-roll derivative Clp and for the aileron effectiveness.
The results of the investigation reported herein were obtained in the rolling-flow test section of the Langley stability tunnel, and the models were those used for the investigation reported in reference 6. The purpose of the present tests was to obtain more complete information, at least at low speeds, on the static and rolling characteristics of the wings and also to obtain a correlation between techniques of the Langley stability tunnel (rolling flow) and the Langley 7- by 10-foot tunnel (free rotation) for determining the damping in roll.
The wings tested were sweptback 3.6°, 32.6°, and 46.7° and had an aspect ratio of 4 and taper ratio of 0.6.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:36:07Z | |
| date available | 2017-09-04T17:36:07Z | |
| date copyright | 01/01/1949 | |
| date issued | 1949 | |
| identifier other | DJSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/158996 | |
| description abstract | INTRODUCTION The influence of a number of different geometric parameters on the rolling stability derivatives of wings have been investigated in the Langley stability tunnel by means of the rolling-flow technique. (See reference 1.) The investigations have included the effects of aspect ratio and sweep (reference 2), taper ratio (reference 3), dihedral (reference 4), and airfoil section (reference 5). All of the investigations were performed at low Mach numbers and with moderately thick wings. In order to obtain an indication of the rolling characteristics of sweptback wings at higher Subsonic speeds, a series of thin wings (NACA 65A006 airfoil section) were tested in the Langley high-speed 7- by 10-foot wind tunnel at Mach numbers from about 0.4 to about 0.9. (See reference 6.) Results were obtained over an angle-of-attack range from 0.3° to 6.5° for the damping-in-roll derivative Clp and for the aileron effectiveness. The results of the investigation reported herein were obtained in the rolling-flow test section of the Langley stability tunnel, and the models were those used for the investigation reported in reference 6. The purpose of the present tests was to obtain more complete information, at least at low speeds, on the static and rolling characteristics of the wings and also to obtain a correlation between techniques of the Langley stability tunnel (rolling flow) and the Langley 7- by 10-foot tunnel (free rotation) for determining the damping in roll. The wings tested were sweptback 3.6°, 32.6°, and 46.7° and had an aspect ratio of 4 and taper ratio of 0.6. | |
| language | English | |
| title | NACA-RM-L9F14 | num |
| title | Effect of sweepback on the low-speed static and rolling stability derivatives of thin tapered wings of aspect ratio 4 | en |
| type | standard | |
| page | 37 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1949 | |
| contenttype | fulltext |