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NACA-RM-L9A07
Low-speed investigation of aileron and spoiler characteristics of a wing having 42 degrees sweepback of the leading edge and circular-arc airfoil sections at Reynolds numbers of approximately 6.0 x 10(exp 6)
Year: 1949
Abstract: INTRODUCTION
The contemplated use of swept wings incorporating sharp-edged air-foil sections for high-speed airplanes has resulted in a need for information concerning the effectiveness of lateral-control devices on wings of this type. An investigation at low air speeds, therefore, has been made in the Langley 19-foot pressure tunnel to determine the lateral characteristics fo a 42° sweptback wing which had sharp-edged, symmetrical, circular-arc airfoil sections and was equipped with either a conventional aileron or various span wise arrangements of step spoilers.
The rolling-moment characteristics of the aileron and the spoilers together with the aileron hinge-moment, normal-force, and balance-chamber pressure characteristics were determined for both the plain wing and the wing equipped with various high-lift and stall-control devices. These devices included extensible, round-nose, leading-edge flaps, leading-edge drooped-nose flaps, trailing-edge split flaps, and upper-surface fences.
The investigation was conducted at Reynolds numbers ranging between 5.3 X 106 and 6.9 X 106 which corresponded to a mach number range of 0.11 to 0.15.
The contemplated use of swept wings incorporating sharp-edged air-foil sections for high-speed airplanes has resulted in a need for information concerning the effectiveness of lateral-control devices on wings of this type. An investigation at low air speeds, therefore, has been made in the Langley 19-foot pressure tunnel to determine the lateral characteristics fo a 42° sweptback wing which had sharp-edged, symmetrical, circular-arc airfoil sections and was equipped with either a conventional aileron or various span wise arrangements of step spoilers.
The rolling-moment characteristics of the aileron and the spoilers together with the aileron hinge-moment, normal-force, and balance-chamber pressure characteristics were determined for both the plain wing and the wing equipped with various high-lift and stall-control devices. These devices included extensible, round-nose, leading-edge flaps, leading-edge drooped-nose flaps, trailing-edge split flaps, and upper-surface fences.
The investigation was conducted at Reynolds numbers ranging between 5.3 X 106 and 6.9 X 106 which corresponded to a mach number range of 0.11 to 0.15.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:23:55Z | |
| date available | 2017-09-04T16:23:55Z | |
| date copyright | 01/01/1949 | |
| date issued | 1949 | |
| identifier other | TTSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/87219 | |
| description abstract | INTRODUCTION The contemplated use of swept wings incorporating sharp-edged air-foil sections for high-speed airplanes has resulted in a need for information concerning the effectiveness of lateral-control devices on wings of this type. An investigation at low air speeds, therefore, has been made in the Langley 19-foot pressure tunnel to determine the lateral characteristics fo a 42° sweptback wing which had sharp-edged, symmetrical, circular-arc airfoil sections and was equipped with either a conventional aileron or various span wise arrangements of step spoilers. The rolling-moment characteristics of the aileron and the spoilers together with the aileron hinge-moment, normal-force, and balance-chamber pressure characteristics were determined for both the plain wing and the wing equipped with various high-lift and stall-control devices. These devices included extensible, round-nose, leading-edge flaps, leading-edge drooped-nose flaps, trailing-edge split flaps, and upper-surface fences. The investigation was conducted at Reynolds numbers ranging between 5.3 X 106 and 6.9 X 106 which corresponded to a mach number range of 0.11 to 0.15. | |
| language | English | |
| title | NACA-RM-L9A07 | num |
| title | Low-speed investigation of aileron and spoiler characteristics of a wing having 42 degrees sweepback of the leading edge and circular-arc airfoil sections at Reynolds numbers of approximately 6.0 x 10(exp 6) | en |
| type | standard | |
| page | 60 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1949 | |
| contenttype | fulltext |