درباره ما
NACA-RM-L9E10
Effects of Mach number and sweep on the damping-in-roll characteristics of wings of aspect ratio 4
Year: 1949
Abstract: INTRODUCTION
Low-speed experimental data and theory (references 1 and 2) indicate an appreciable reduction in the damping-in-roll properties of a wing as the sweep angle is increased. The theoretical manner in which these effects are affected by compressibility is treated in references 2 and 3. Little experimental data, however, are available a t high-subsonic Mach numbers for comparison with theory. Accordingly, an extensive investigation is being conducted in the Langley high-sped 7- by 10-foot tunnel to determine the effects of sweep angle and Mach number on the damping-in-roll characteristics of a series of wings. The first wing investigated was a 35° sweptback wing of aspect ratio 3, and the damping-roll characteristics of this wing at high-subsonic Mach numbers are presented in reference 4.
The present paper presents the results of an experimental determination of the damping-in-roll characteristics of three wings of aspect ratio 4 and taper ratio 0.6 with sweep angles of 3.6°, 32.6°, and 46.7° referred to the quarter-chord line. The investigation utilized the free-roll technique described in reference 4 and the tests were made at angles of attack of 0.30°, 3.45°, and 6.5° through a Mach number range from 0.40 to 0.91. This paper also includes a comparison with theoretical results computed from Weissinger's theory as presented in reference 2 and from the more approximate, but more convenient, theory of reference 3.
Low-speed experimental data and theory (references 1 and 2) indicate an appreciable reduction in the damping-in-roll properties of a wing as the sweep angle is increased. The theoretical manner in which these effects are affected by compressibility is treated in references 2 and 3. Little experimental data, however, are available a t high-subsonic Mach numbers for comparison with theory. Accordingly, an extensive investigation is being conducted in the Langley high-sped 7- by 10-foot tunnel to determine the effects of sweep angle and Mach number on the damping-in-roll characteristics of a series of wings. The first wing investigated was a 35° sweptback wing of aspect ratio 3, and the damping-roll characteristics of this wing at high-subsonic Mach numbers are presented in reference 4.
The present paper presents the results of an experimental determination of the damping-in-roll characteristics of three wings of aspect ratio 4 and taper ratio 0.6 with sweep angles of 3.6°, 32.6°, and 46.7° referred to the quarter-chord line. The investigation utilized the free-roll technique described in reference 4 and the tests were made at angles of attack of 0.30°, 3.45°, and 6.5° through a Mach number range from 0.40 to 0.91. This paper also includes a comparison with theoretical results computed from Weissinger's theory as presented in reference 2 and from the more approximate, but more convenient, theory of reference 3.
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:29:22Z | |
| date available | 2017-09-04T16:29:22Z | |
| date copyright | 01/01/1949 | |
| date issued | 1949 | |
| identifier other | UISWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/92621 | |
| description abstract | INTRODUCTION Low-speed experimental data and theory (references 1 and 2) indicate an appreciable reduction in the damping-in-roll properties of a wing as the sweep angle is increased. The theoretical manner in which these effects are affected by compressibility is treated in references 2 and 3. Little experimental data, however, are available a t high-subsonic Mach numbers for comparison with theory. Accordingly, an extensive investigation is being conducted in the Langley high-sped 7- by 10-foot tunnel to determine the effects of sweep angle and Mach number on the damping-in-roll characteristics of a series of wings. The first wing investigated was a 35° sweptback wing of aspect ratio 3, and the damping-roll characteristics of this wing at high-subsonic Mach numbers are presented in reference 4. The present paper presents the results of an experimental determination of the damping-in-roll characteristics of three wings of aspect ratio 4 and taper ratio 0.6 with sweep angles of 3.6°, 32.6°, and 46.7° referred to the quarter-chord line. The investigation utilized the free-roll technique described in reference 4 and the tests were made at angles of attack of 0.30°, 3.45°, and 6.5° through a Mach number range from 0.40 to 0.91. This paper also includes a comparison with theoretical results computed from Weissinger's theory as presented in reference 2 and from the more approximate, but more convenient, theory of reference 3. | |
| language | English | |
| title | NACA-RM-L9E10 | num |
| title | Effects of Mach number and sweep on the damping-in-roll characteristics of wings of aspect ratio 4 | en |
| type | standard | |
| page | 29 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1949 | |
| contenttype | fulltext |