درباره ما
NACA-RM-L52C11
Low-speed longitudinal aerodynamic characteristics of a twisted and cambered wing of 45 degrees sweepback and aspect ratio 8 with and without high-lift and stall-control devices and a fuselage at Reynolds numbers from 1.5 x 10(exp 6) to 4.8 x 10(exp 6)
Year: 1952
Abstract: INTRODUCTION
As part of a broad program to investigate the low-speed aerodynamic characteristics of sweptback wings, the static longitudinal stability characteristics of a 450 sweptback wing of aspect ratio 8.0 were investigated in the Langley 19-foot pressure tunnel. The results are reported in references 1 to 3. Although a wing of such plan form is basically very unstable at moderate and high lift coefficients, it was pointed out in reference 1 that longitudinal stability could be obtained from the use of stall-control devices.
More recently, consideration has been given to the use of camber and twist variations along the span as a means of counteracting the undesirable induced effects of sweepback. Camber and twist also provide additional advantages, if properly applied, in that both the profile and induced drag would be reduced for high design lift coefficients.
With these considerations in mind, an experimental investigation was conducted to determine the low-speed longitudinal characteristics of a 450 sweptback wing of aspect ratio 8.0, which was cambered and twisted to provide an elliptical spanwise load distribution at a design lift coefficient of 0.7 and a Mach number of 0.9. The plan form of the present wing was similar to the plan form of the wing reported in references 1 to 3, which had no camber or twist.
The present paper contains the results of force tests to determine the effects of high-lift and stall-control devices on the cambered and twisted wing. The investigation was conducted at Reynolds numbers ranging from 1.5 x 106 to 4.8 x 106.
As part of a broad program to investigate the low-speed aerodynamic characteristics of sweptback wings, the static longitudinal stability characteristics of a 450 sweptback wing of aspect ratio 8.0 were investigated in the Langley 19-foot pressure tunnel. The results are reported in references 1 to 3. Although a wing of such plan form is basically very unstable at moderate and high lift coefficients, it was pointed out in reference 1 that longitudinal stability could be obtained from the use of stall-control devices.
More recently, consideration has been given to the use of camber and twist variations along the span as a means of counteracting the undesirable induced effects of sweepback. Camber and twist also provide additional advantages, if properly applied, in that both the profile and induced drag would be reduced for high design lift coefficients.
With these considerations in mind, an experimental investigation was conducted to determine the low-speed longitudinal characteristics of a 450 sweptback wing of aspect ratio 8.0, which was cambered and twisted to provide an elliptical spanwise load distribution at a design lift coefficient of 0.7 and a Mach number of 0.9. The plan form of the present wing was similar to the plan form of the wing reported in references 1 to 3, which had no camber or twist.
The present paper contains the results of force tests to determine the effects of high-lift and stall-control devices on the cambered and twisted wing. The investigation was conducted at Reynolds numbers ranging from 1.5 x 106 to 4.8 x 106.
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:37:18Z | |
| date available | 2017-09-04T17:37:18Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | DMSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/160186 | |
| description abstract | INTRODUCTION As part of a broad program to investigate the low-speed aerodynamic characteristics of sweptback wings, the static longitudinal stability characteristics of a 450 sweptback wing of aspect ratio 8.0 were investigated in the Langley 19-foot pressure tunnel. The results are reported in references 1 to 3. Although a wing of such plan form is basically very unstable at moderate and high lift coefficients, it was pointed out in reference 1 that longitudinal stability could be obtained from the use of stall-control devices. More recently, consideration has been given to the use of camber and twist variations along the span as a means of counteracting the undesirable induced effects of sweepback. Camber and twist also provide additional advantages, if properly applied, in that both the profile and induced drag would be reduced for high design lift coefficients. With these considerations in mind, an experimental investigation was conducted to determine the low-speed longitudinal characteristics of a 450 sweptback wing of aspect ratio 8.0, which was cambered and twisted to provide an elliptical spanwise load distribution at a design lift coefficient of 0.7 and a Mach number of 0.9. The plan form of the present wing was similar to the plan form of the wing reported in references 1 to 3, which had no camber or twist. The present paper contains the results of force tests to determine the effects of high-lift and stall-control devices on the cambered and twisted wing. The investigation was conducted at Reynolds numbers ranging from 1.5 x 106 to 4.8 x 106. | |
| language | English | |
| title | NACA-RM-L52C11 | num |
| title | Low-speed longitudinal aerodynamic characteristics of a twisted and cambered wing of 45 degrees sweepback and aspect ratio 8 with and without high-lift and stall-control devices and a fuselage at Reynolds numbers from 1.5 x 10(exp 6) to 4.8 x 10(exp 6) | en |
| type | standard | |
| page | 78 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |