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NACA-RM-A51G31
The forces and pressure distribution at subsonic speeds on a plane wing having 45 degrees of sweepback, an aspect ratio of 3, and a taper ratio of 0.5
Year: 1951
Abstract: INTRODUCTION
Wings having moderately high degrees of sweepback offer the possibility of flight at transonic speeds without serious compressibility effects. Studies of the pressure distributions on such wings have shown that simple sweep theory does not offer an adequate method of predicting the chordwise distribution of pressure near the roots or the tips of the tings. For swept-back wings of low aspect ratio, a substantial part of the wing surface is subjected to flow characteristics which result from the so-called root and tip effects. Experimental determination of the pressure distribution on such wings will provide not only detailed information concerning the aerodynamic characteristics, but also till furnish data for evaluating and extending the theoretical methods for computing surface pressures.
An Investigation has been conducted in the Ames 12-foot pressure wind tunnel throughout a wide range of Reynolds numbers and subsonic Mach numbers to obtain experimentally the pressure distribution and the total lift, drag, and pitching moment on a wing having 45° of sweepback and an aspect ratio of 3. To determine the effects of both Mach number and Reynolds number, the wing was tested at constant Reynolds numbers over a range of Mach numbers and at a constant Mach number over a range of Reynolds numbers. The force data and a representative portion of the pressure data are presented in graphic form along with a limited analysis of the data. The complete pressure data for the ting are presented in tabular form.
Wings having moderately high degrees of sweepback offer the possibility of flight at transonic speeds without serious compressibility effects. Studies of the pressure distributions on such wings have shown that simple sweep theory does not offer an adequate method of predicting the chordwise distribution of pressure near the roots or the tips of the tings. For swept-back wings of low aspect ratio, a substantial part of the wing surface is subjected to flow characteristics which result from the so-called root and tip effects. Experimental determination of the pressure distribution on such wings will provide not only detailed information concerning the aerodynamic characteristics, but also till furnish data for evaluating and extending the theoretical methods for computing surface pressures.
An Investigation has been conducted in the Ames 12-foot pressure wind tunnel throughout a wide range of Reynolds numbers and subsonic Mach numbers to obtain experimentally the pressure distribution and the total lift, drag, and pitching moment on a wing having 45° of sweepback and an aspect ratio of 3. To determine the effects of both Mach number and Reynolds number, the wing was tested at constant Reynolds numbers over a range of Mach numbers and at a constant Mach number over a range of Reynolds numbers. The force data and a representative portion of the pressure data are presented in graphic form along with a limited analysis of the data. The complete pressure data for the ting are presented in tabular form.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:42:56Z | |
| date available | 2017-09-04T15:42:56Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | PKMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/45092 | |
| description abstract | INTRODUCTION Wings having moderately high degrees of sweepback offer the possibility of flight at transonic speeds without serious compressibility effects. Studies of the pressure distributions on such wings have shown that simple sweep theory does not offer an adequate method of predicting the chordwise distribution of pressure near the roots or the tips of the tings. For swept-back wings of low aspect ratio, a substantial part of the wing surface is subjected to flow characteristics which result from the so-called root and tip effects. Experimental determination of the pressure distribution on such wings will provide not only detailed information concerning the aerodynamic characteristics, but also till furnish data for evaluating and extending the theoretical methods for computing surface pressures. An Investigation has been conducted in the Ames 12-foot pressure wind tunnel throughout a wide range of Reynolds numbers and subsonic Mach numbers to obtain experimentally the pressure distribution and the total lift, drag, and pitching moment on a wing having 45° of sweepback and an aspect ratio of 3. To determine the effects of both Mach number and Reynolds number, the wing was tested at constant Reynolds numbers over a range of Mach numbers and at a constant Mach number over a range of Reynolds numbers. The force data and a representative portion of the pressure data are presented in graphic form along with a limited analysis of the data. The complete pressure data for the ting are presented in tabular form. | |
| language | English | |
| title | NACA-RM-A51G31 | num |
| title | The forces and pressure distribution at subsonic speeds on a plane wing having 45 degrees of sweepback, an aspect ratio of 3, and a taper ratio of 0.5 | en |
| type | standard | |
| page | 161 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext |