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NACA-TN-2775
Effect of linear spanwise variations of twist and circular-arc camber on low-speed static stability, rolling, and yawing characteristics of a 45 degree sweptback wing of aspect ratio 4 and taper ratio 0.6
Year: 1952
Abstract: An investigation at law scale has been made in the Langley stability tunnel in order to determine the effect of linear spanwise variations of twist and circular-arc camber the low-speed aerodynamic characteristics and static-stability and rotary-stability (rolling and yawing) derivatives of a wing of aspect ratio 4, taper ratio O.6, and with 45° sweepback of the quarter-chord line.
Results of the investigation indicate that twist or camber produced only small changes in the maximum lift coefficient. A combination of camber and twist was more effective than twist alone in providing an increase in the maximum lift-to-drag ratio in the moderate lift-coefficient range for the investigated. The variation of static longitudinal stability through the lift-coefficient range was less for the twisted wing than for the twisted end cambered plane wing
Results of the investigation indicate that twist or camber produced only small changes in the maximum lift coefficient. A combination of camber and twist was more effective than twist alone in providing an increase in the maximum lift-to-drag ratio in the moderate lift-coefficient range for the investigated. The variation of static longitudinal stability through the lift-coefficient range was less for the twisted wing than for the twisted end cambered plane wing
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:02:46Z | |
| date available | 2017-09-04T18:02:46Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | GCOUYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/185716 | |
| description abstract | An investigation at law scale has been made in the Langley stability tunnel in order to determine the effect of linear spanwise variations of twist and circular-arc camber the low-speed aerodynamic characteristics and static-stability and rotary-stability (rolling and yawing) derivatives of a wing of aspect ratio 4, taper ratio O.6, and with 45° sweepback of the quarter-chord line. Results of the investigation indicate that twist or camber produced only small changes in the maximum lift coefficient. A combination of camber and twist was more effective than twist alone in providing an increase in the maximum lift-to-drag ratio in the moderate lift-coefficient range for the investigated. The variation of static longitudinal stability through the lift-coefficient range was less for the twisted wing than for the twisted end cambered plane wing | |
| language | English | |
| title | NACA-TN-2775 | num |
| title | Effect of linear spanwise variations of twist and circular-arc camber on low-speed static stability, rolling, and yawing characteristics of a 45 degree sweptback wing of aspect ratio 4 and taper ratio 0.6 | en |
| type | standard | |
| page | 28 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |