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NACA-TN-2819
Effect of high-lift devices on the static-lateral-stability derivatives of a 45 degree sweptback wing of aspect ratio 4.0 and taper ratio 0.6 in combination with a body
Year: 1952
Abstract: An investigation has been made in the Langley stability tunnel to determine the effect of high-lift devices on the low-speed static-lateral-stability derivatives of a 45x sweptback wing of aspect ration 4.0 and taper ratio 0.6. Comparison between the increments in the static-lateral-stability derivatives due to flap deflections obtained fro experiment and the increments evaluated by a simple sweep theory is also made.
The results of the investigation show that, for moderate and high-lift coefficients, an increase in trailing-edge flap span, with or without a leading-edge slat, generally resulted in increased effective dihedral and directional stability. The leading-edge slats tended mainly to extend the trends obtained at low lift coefficients for the dihedral effect to nearer maximum lift. An application of simple sweep theory and measured lift and drag increments to the evaluation of the increments in the static-lateral-stability derivatives due to trailing-edge flaps indicates that the trend and approximate magnitude of the variation of these increments with flap span are predicted in the moderate and high lift-coefficient range.
The results of the investigation show that, for moderate and high-lift coefficients, an increase in trailing-edge flap span, with or without a leading-edge slat, generally resulted in increased effective dihedral and directional stability. The leading-edge slats tended mainly to extend the trends obtained at low lift coefficients for the dihedral effect to nearer maximum lift. An application of simple sweep theory and measured lift and drag increments to the evaluation of the increments in the static-lateral-stability derivatives due to trailing-edge flaps indicates that the trend and approximate magnitude of the variation of these increments with flap span are predicted in the moderate and high lift-coefficient range.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:32:53Z | |
| date available | 2017-09-04T18:32:53Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | JCOUYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;query=author:%22NAVY%20-%206159DD6E273C9FCD0Facil/handle/yse/215085 | |
| description abstract | An investigation has been made in the Langley stability tunnel to determine the effect of high-lift devices on the low-speed static-lateral-stability derivatives of a 45x sweptback wing of aspect ration 4.0 and taper ratio 0.6. Comparison between the increments in the static-lateral-stability derivatives due to flap deflections obtained fro experiment and the increments evaluated by a simple sweep theory is also made. The results of the investigation show that, for moderate and high-lift coefficients, an increase in trailing-edge flap span, with or without a leading-edge slat, generally resulted in increased effective dihedral and directional stability. The leading-edge slats tended mainly to extend the trends obtained at low lift coefficients for the dihedral effect to nearer maximum lift. An application of simple sweep theory and measured lift and drag increments to the evaluation of the increments in the static-lateral-stability derivatives due to trailing-edge flaps indicates that the trend and approximate magnitude of the variation of these increments with flap span are predicted in the moderate and high lift-coefficient range. | |
| language | English | |
| title | NACA-TN-2819 | num |
| title | Effect of high-lift devices on the static-lateral-stability derivatives of a 45 degree sweptback wing of aspect ratio 4.0 and taper ratio 0.6 in combination with a body | en |
| type | standard | |
| page | 51 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |