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NACA-RM-A52D22
The forces and pressure distribution at subsonic speeds on a cambered and twisted wing having 45 degrees of sweepback and aspect ratio of 3 and a taper ratio of 0.5
Year: 1952
Abstract: INTRODUCTION
The use of camber and twist as a means of improving the aerodynamic characteristics of 8wept-back wings with moderately thin airfoil sections has received considerable attention. While some force and pressure data have been obtained showing the effects of camber and twist on the aerodynamic characteristics of swept-back wings at low speeds (e.g., references 1 and 2), the available pressure data at high subsonic Mach numbers are rather limited, particularly for swept-back wings of low aspect ratio.
The results of pressure-distribution and force tests of an unhampered and untwisted wing having the quarter-chord line swept back 450 an aspect ratio of 3.0, and a taper ratio of 0.5 have been reported in reference 3. The results of similar tests of a cambered and twisted wing having the same plan form are presented herein. Both wings were tested in the Ames 12-foot pressure wind tunnel over wide ranges of Reynolds numbers and subsonic mach numbers. The complete pressure distribution data are presented in tabular form. Portions of the data from reference 3 have been included in the present report for purposes of comparison.
The use of camber and twist as a means of improving the aerodynamic characteristics of 8wept-back wings with moderately thin airfoil sections has received considerable attention. While some force and pressure data have been obtained showing the effects of camber and twist on the aerodynamic characteristics of swept-back wings at low speeds (e.g., references 1 and 2), the available pressure data at high subsonic Mach numbers are rather limited, particularly for swept-back wings of low aspect ratio.
The results of pressure-distribution and force tests of an unhampered and untwisted wing having the quarter-chord line swept back 450 an aspect ratio of 3.0, and a taper ratio of 0.5 have been reported in reference 3. The results of similar tests of a cambered and twisted wing having the same plan form are presented herein. Both wings were tested in the Ames 12-foot pressure wind tunnel over wide ranges of Reynolds numbers and subsonic mach numbers. The complete pressure distribution data are presented in tabular form. Portions of the data from reference 3 have been included in the present report for purposes of comparison.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:08:35Z | |
| date available | 2017-09-04T16:08:35Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | SEMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/71795 | |
| description abstract | INTRODUCTION The use of camber and twist as a means of improving the aerodynamic characteristics of 8wept-back wings with moderately thin airfoil sections has received considerable attention. While some force and pressure data have been obtained showing the effects of camber and twist on the aerodynamic characteristics of swept-back wings at low speeds (e.g., references 1 and 2), the available pressure data at high subsonic Mach numbers are rather limited, particularly for swept-back wings of low aspect ratio. The results of pressure-distribution and force tests of an unhampered and untwisted wing having the quarter-chord line swept back 450 an aspect ratio of 3.0, and a taper ratio of 0.5 have been reported in reference 3. The results of similar tests of a cambered and twisted wing having the same plan form are presented herein. Both wings were tested in the Ames 12-foot pressure wind tunnel over wide ranges of Reynolds numbers and subsonic mach numbers. The complete pressure distribution data are presented in tabular form. Portions of the data from reference 3 have been included in the present report for purposes of comparison. | |
| language | English | |
| title | NACA-RM-A52D22 | num |
| title | The forces and pressure distribution at subsonic speeds on a cambered and twisted wing having 45 degrees of sweepback and aspect ratio of 3 and a taper ratio of 0.5 | en |
| type | standard | |
| page | 167 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |