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NACA-RM-L50F20
Effects of leading-edge devices and trailing-edge flaps on longitudinal characteristics of two 47.7 degrees sweptback wings of aspect ratios 5.1 and 6.0 at a Reynolds number of 6.0 x 10(exp 6)
Year: 1950
Abstract: INTRODUCTION
In order to increase the range of highly sweptback-wing aircraft, it becomes desirable to use wings of large aspect ratio. Reference 1 points out, however, that highly swept wings of large aspect ratio have inherently poor longitudinal stability characteristics and, therefore, the problem of in stability in the high angle-of-attack range must be considered. However, the possibility of eliminating the longitudinal instability of sweptback wings by means of leading-edge devices has been shown by previous investigations, such as references 2 and 3. Furthermore, the low effectiveness of ordinary split trailing - edge flaps on highly swept wings indicates the desirability of investigating other types of flaps.
With these considerations in mind, an investigation was conducted in the Langley 19-foot pressure tunnel to determine the effectiveness of leading-edge devices and double slotted trailing-edge flaps on two wings of 47.7° of sweepback and aspect ratios of 5.1 and 6.0 with NACA 64-210 airfoil sections normal to the 0.286-chord line. Most of the data were obtained at a Reynolds number of approximately 6.0 x 10 6 (Mach number of 0.14). The longitudinal characteristics of the plain wings have been previously reported in reference 4. The results of a similar investigation on a 47.5° sweptback wing of aspect ratio 3.4 are reported in reference 5.
In order to increase the range of highly sweptback-wing aircraft, it becomes desirable to use wings of large aspect ratio. Reference 1 points out, however, that highly swept wings of large aspect ratio have inherently poor longitudinal stability characteristics and, therefore, the problem of in stability in the high angle-of-attack range must be considered. However, the possibility of eliminating the longitudinal instability of sweptback wings by means of leading-edge devices has been shown by previous investigations, such as references 2 and 3. Furthermore, the low effectiveness of ordinary split trailing - edge flaps on highly swept wings indicates the desirability of investigating other types of flaps.
With these considerations in mind, an investigation was conducted in the Langley 19-foot pressure tunnel to determine the effectiveness of leading-edge devices and double slotted trailing-edge flaps on two wings of 47.7° of sweepback and aspect ratios of 5.1 and 6.0 with NACA 64-210 airfoil sections normal to the 0.286-chord line. Most of the data were obtained at a Reynolds number of approximately 6.0 x 10 6 (Mach number of 0.14). The longitudinal characteristics of the plain wings have been previously reported in reference 4. The results of a similar investigation on a 47.5° sweptback wing of aspect ratio 3.4 are reported in reference 5.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:38:57Z | |
| date available | 2017-09-04T16:38:57Z | |
| date copyright | 01/01/1950 | |
| date issued | 1950 | |
| identifier other | VJSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/102558 | |
| description abstract | INTRODUCTION In order to increase the range of highly sweptback-wing aircraft, it becomes desirable to use wings of large aspect ratio. Reference 1 points out, however, that highly swept wings of large aspect ratio have inherently poor longitudinal stability characteristics and, therefore, the problem of in stability in the high angle-of-attack range must be considered. However, the possibility of eliminating the longitudinal instability of sweptback wings by means of leading-edge devices has been shown by previous investigations, such as references 2 and 3. Furthermore, the low effectiveness of ordinary split trailing - edge flaps on highly swept wings indicates the desirability of investigating other types of flaps. With these considerations in mind, an investigation was conducted in the Langley 19-foot pressure tunnel to determine the effectiveness of leading-edge devices and double slotted trailing-edge flaps on two wings of 47.7° of sweepback and aspect ratios of 5.1 and 6.0 with NACA 64-210 airfoil sections normal to the 0.286-chord line. Most of the data were obtained at a Reynolds number of approximately 6.0 x 10 6 (Mach number of 0.14). The longitudinal characteristics of the plain wings have been previously reported in reference 4. The results of a similar investigation on a 47.5° sweptback wing of aspect ratio 3.4 are reported in reference 5. | |
| language | English | |
| title | NACA-RM-L50F20 | num |
| title | Effects of leading-edge devices and trailing-edge flaps on longitudinal characteristics of two 47.7 degrees sweptback wings of aspect ratios 5.1 and 6.0 at a Reynolds number of 6.0 x 10(exp 6) | en |
| type | standard | |
| page | 106 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1950 | |
| contenttype | fulltext |