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NACA-RM-L51K26
Force and pressure investigation at large scale of a 49 degrees sweptback semispan wing having NACA 65A006 sections and equipped with various slat arrangements
Year: 1952
Abstract: INTRODUCTION
The usefulness of slats in improving the low-speed characteristics of sweptback wings has been demonstrated in several investigations of specific high-speed plan forms. (see, for example, references 1 and 2.) inasmuch as the flow characteristics for a sweptback wing change considerably with variations in wing sweep and airfoil profile, the stall-control-device requirements (both aerodynamic and structural) for sweptback wings will also vary with wing geometry.
In order to augment the limited amount of available low-speed, large-scale, slat data on swept wings, an investigation was conducted span 49.1º sweptback wing . The wing has an aspect ration of 3.78 and incorporates NACA 65A006 airfoil sections streamwise. The longitudinal and deflection angles. In addition, chordwise pressure distributions were determined from pressure orifices located on the wing and on the extended slat. Most of the data were measured at a Reynolds number of 6.1x106 and at a Mach number of 0.10.
The usefulness of slats in improving the low-speed characteristics of sweptback wings has been demonstrated in several investigations of specific high-speed plan forms. (see, for example, references 1 and 2.) inasmuch as the flow characteristics for a sweptback wing change considerably with variations in wing sweep and airfoil profile, the stall-control-device requirements (both aerodynamic and structural) for sweptback wings will also vary with wing geometry.
In order to augment the limited amount of available low-speed, large-scale, slat data on swept wings, an investigation was conducted span 49.1º sweptback wing . The wing has an aspect ration of 3.78 and incorporates NACA 65A006 airfoil sections streamwise. The longitudinal and deflection angles. In addition, chordwise pressure distributions were determined from pressure orifices located on the wing and on the extended slat. Most of the data were measured at a Reynolds number of 6.1x106 and at a Mach number of 0.10.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:34:09Z | |
| date available | 2017-09-04T15:34:09Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | OLSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/35878 | |
| description abstract | INTRODUCTION The usefulness of slats in improving the low-speed characteristics of sweptback wings has been demonstrated in several investigations of specific high-speed plan forms. (see, for example, references 1 and 2.) inasmuch as the flow characteristics for a sweptback wing change considerably with variations in wing sweep and airfoil profile, the stall-control-device requirements (both aerodynamic and structural) for sweptback wings will also vary with wing geometry. In order to augment the limited amount of available low-speed, large-scale, slat data on swept wings, an investigation was conducted span 49.1º sweptback wing . The wing has an aspect ration of 3.78 and incorporates NACA 65A006 airfoil sections streamwise. The longitudinal and deflection angles. In addition, chordwise pressure distributions were determined from pressure orifices located on the wing and on the extended slat. Most of the data were measured at a Reynolds number of 6.1x106 and at a Mach number of 0.10. | |
| language | English | |
| title | NACA-RM-L51K26 | num |
| title | Force and pressure investigation at large scale of a 49 degrees sweptback semispan wing having NACA 65A006 sections and equipped with various slat arrangements | en |
| type | standard | |
| page | 62 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |