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NACA-RM-A51D27
Characteristics throughout the subsonic speed range of a plane wing and of a cambered and twisted wing, both having 45 degrees of sweepback
Year: 1951
Abstract: INTRODUCTION
Theoretical studies and a number of experimental investigations have indicated that camber and twist may improve the characteristics h. of swept wings. This improvement results from more uniform distribution of load, both spanwise and chord wise, which alleviates the flow separation and the attendant stability and drag deterioration at moderate ate and high lift coefficients. That such improvement is obtainable through the use of camber and twist has been demonstrated by the low speed investigation reported in references land 2. To extend the study of the effects of camber and twist, an investigation has been made in the Ames W-foot pressure wind tunnel at Mach rubbers up to 0.94 of two 45° swept-back wings similar to those reported in references 1 and 2.1 One of the wings had no twist and the wing profile was symmetrical. The other wing was cambered for a design wing-lift coefficient of 0.4 and twisted to relieve the loading at the tip which accompanies sweepback.
Theoretical studies and a number of experimental investigations have indicated that camber and twist may improve the characteristics h. of swept wings. This improvement results from more uniform distribution of load, both spanwise and chord wise, which alleviates the flow separation and the attendant stability and drag deterioration at moderate ate and high lift coefficients. That such improvement is obtainable through the use of camber and twist has been demonstrated by the low speed investigation reported in references land 2. To extend the study of the effects of camber and twist, an investigation has been made in the Ames W-foot pressure wind tunnel at Mach rubbers up to 0.94 of two 45° swept-back wings similar to those reported in references 1 and 2.1 One of the wings had no twist and the wing profile was symmetrical. The other wing was cambered for a design wing-lift coefficient of 0.4 and twisted to relieve the loading at the tip which accompanies sweepback.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:16:44Z | |
| date available | 2017-09-04T15:16:44Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | MKMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/15999 | |
| description abstract | INTRODUCTION Theoretical studies and a number of experimental investigations have indicated that camber and twist may improve the characteristics h. of swept wings. This improvement results from more uniform distribution of load, both spanwise and chord wise, which alleviates the flow separation and the attendant stability and drag deterioration at moderate ate and high lift coefficients. That such improvement is obtainable through the use of camber and twist has been demonstrated by the low speed investigation reported in references land 2. To extend the study of the effects of camber and twist, an investigation has been made in the Ames W-foot pressure wind tunnel at Mach rubbers up to 0.94 of two 45° swept-back wings similar to those reported in references 1 and 2.1 One of the wings had no twist and the wing profile was symmetrical. The other wing was cambered for a design wing-lift coefficient of 0.4 and twisted to relieve the loading at the tip which accompanies sweepback. | |
| language | English | |
| title | NACA-RM-A51D27 | num |
| title | Characteristics throughout the subsonic speed range of a plane wing and of a cambered and twisted wing, both having 45 degrees of sweepback | en |
| type | standard | |
| page | 124 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext |