درباره ما
NACA-RM-A8D20
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : subsonic Mach and Reynolds number effects on the characteristics of the wing and on the effectiveness of an elevon
Year: 1948
Abstract: A wind-tunnel investigation has been made of a semispan model of a wing swept back 63° having an aspect ratio of 3.5 and a taper ratio (tip chord/root chord) of 0.25. These were conducted to evaluate the effects of Reynolds number and Mach number on the aerodynamic characteristics of the wing. Included in the investigation were measurements of the effectiveness of an elevon used as a longitudinal control.
The aerodynamic center of the wing shifted rearward near a lift coefficient of 0.2; whereas above a lift coefficient of approximately 0.4 there was an abrupt forward shift of the aerodynamic center.
The aerodynamic center of the wing shifted rearward near a lift coefficient of 0.2; whereas above a lift coefficient of approximately 0.4 there was an abrupt forward shift of the aerodynamic center.
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:23:38Z | |
| date available | 2017-09-04T16:23:38Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | TTFNKEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/87025 | |
| description abstract | A wind-tunnel investigation has been made of a semispan model of a wing swept back 63° having an aspect ratio of 3.5 and a taper ratio (tip chord/root chord) of 0.25. These were conducted to evaluate the effects of Reynolds number and Mach number on the aerodynamic characteristics of the wing. Included in the investigation were measurements of the effectiveness of an elevon used as a longitudinal control. The aerodynamic center of the wing shifted rearward near a lift coefficient of 0.2; whereas above a lift coefficient of approximately 0.4 there was an abrupt forward shift of the aerodynamic center. | |
| language | English | |
| title | NACA-RM-A8D20 | num |
| title | Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : subsonic Mach and Reynolds number effects on the characteristics of the wing and on the effectiveness of an elevon | en |
| type | standard | |
| page | 58 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext |