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NACA-RM-L9E24
Investigation of low-speed aileron control characteristics at a Reynolds number of 6,800,000 of a wing with leading edge swept back 42 degrees with and without high-lift devices
Year: 1949
Abstract: INTRODUCTION
One of the many low-speed problems associated with the use of highly swept wings is the difficulty in providing adequate lateral control, particularly in the region of maximum lift. Present-day experimental data on the aileron lateral control characteristics of swept wings are largely limited to low-scale results such as reported in reference 1. In order t o provide data at high Reynolds numbers, an investigation of the low-speed aileron control characteristics of swept wings has been undertaken in the Langley 19-foot pressure tunnel. As a part of the lateral-control investigation at large scale, the aileron control characteristics of a 42° sweptback wing incorporating circular sections and of a 37° sweptback wing incorporating NACA 641-212 sections have been presented in references 2 and 3, respectively.
The lateral control characteristics for a 42° sweptback wing fitted with a 20-percent-chord half-span outboard aileron are presented in this paper. The wing incorporated. NACA 641-112 sections perpendicular to the 0.273 chord line and had an aspect ratio of 4.01 and taper ratio of 0.625. The aileron lateral control characteristics are presented together with the aileron load characteristics and balance-chamber pressure for the plain wing and for the equipped with high-lift and stall-control devices. These devices included extensible round-nose leading-edge flap, trailing-edge split flaps, and upper surface fences.
The investigation was carried out at a Reynolds number of 6,800,000, and a Mach number of approximately 0.16 for an angle-of-attack range from -4 through the stall.
One of the many low-speed problems associated with the use of highly swept wings is the difficulty in providing adequate lateral control, particularly in the region of maximum lift. Present-day experimental data on the aileron lateral control characteristics of swept wings are largely limited to low-scale results such as reported in reference 1. In order t o provide data at high Reynolds numbers, an investigation of the low-speed aileron control characteristics of swept wings has been undertaken in the Langley 19-foot pressure tunnel. As a part of the lateral-control investigation at large scale, the aileron control characteristics of a 42° sweptback wing incorporating circular sections and of a 37° sweptback wing incorporating NACA 641-212 sections have been presented in references 2 and 3, respectively.
The lateral control characteristics for a 42° sweptback wing fitted with a 20-percent-chord half-span outboard aileron are presented in this paper. The wing incorporated. NACA 641-112 sections perpendicular to the 0.273 chord line and had an aspect ratio of 4.01 and taper ratio of 0.625. The aileron lateral control characteristics are presented together with the aileron load characteristics and balance-chamber pressure for the plain wing and for the equipped with high-lift and stall-control devices. These devices included extensible round-nose leading-edge flap, trailing-edge split flaps, and upper surface fences.
The investigation was carried out at a Reynolds number of 6,800,000, and a Mach number of approximately 0.16 for an angle-of-attack range from -4 through the stall.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:58:13Z | |
| date available | 2017-09-04T16:58:13Z | |
| date copyright | 01/01/1949 | |
| date issued | 1949 | |
| identifier other | XISWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/121654 | |
| description abstract | INTRODUCTION One of the many low-speed problems associated with the use of highly swept wings is the difficulty in providing adequate lateral control, particularly in the region of maximum lift. Present-day experimental data on the aileron lateral control characteristics of swept wings are largely limited to low-scale results such as reported in reference 1. In order t o provide data at high Reynolds numbers, an investigation of the low-speed aileron control characteristics of swept wings has been undertaken in the Langley 19-foot pressure tunnel. As a part of the lateral-control investigation at large scale, the aileron control characteristics of a 42° sweptback wing incorporating circular sections and of a 37° sweptback wing incorporating NACA 641-212 sections have been presented in references 2 and 3, respectively. The lateral control characteristics for a 42° sweptback wing fitted with a 20-percent-chord half-span outboard aileron are presented in this paper. The wing incorporated. NACA 641-112 sections perpendicular to the 0.273 chord line and had an aspect ratio of 4.01 and taper ratio of 0.625. The aileron lateral control characteristics are presented together with the aileron load characteristics and balance-chamber pressure for the plain wing and for the equipped with high-lift and stall-control devices. These devices included extensible round-nose leading-edge flap, trailing-edge split flaps, and upper surface fences. The investigation was carried out at a Reynolds number of 6,800,000, and a Mach number of approximately 0.16 for an angle-of-attack range from -4 through the stall. | |
| language | English | |
| title | NACA-RM-L9E24 | num |
| title | Investigation of low-speed aileron control characteristics at a Reynolds number of 6,800,000 of a wing with leading edge swept back 42 degrees with and without high-lift devices | en |
| type | standard | |
| page | 33 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1949 | |
| contenttype | fulltext |