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NACA-RM-L53J21
Wind-tunnel investigation at transonic speeds of a spoiler-slot-deflector combination on an unswept NACA 65A006 wing
Year: 1953
Abstract: INTRODUCTION
The spoiler used as a lateral-control device has been the subject of considerable investigation at low and high speeds, and on both swept and unswept wings (refs. 1 to 3). Recent investigations of spoilers used as lateral-control devices have shown that on thin wings with small leading-edge radii the unvented spoiler loses effectiveness rapidly as the angle of attack is increased above 8° (refs. 2 and 3). However, investigations at low and high subsonic speeds as reported in references 3 to 5 have shown that this loss in effectiveness at the higher angles of attack could be substantially reduced by using a slot in the wing behind the spoiler that would allow the air to flow through the wing from the lower to the upper surface when the spoiler was deflected.
The purpose of this investigation was to extend through the transonic speed range previous low and high subsonic speed investigations of spoiler-slut-deflector devices for lateral control. The investigation was made in the Langley high-speed 7- by 10-foot tunnel using the transonic bump to obtain Mach numbers from 0.62 to 1.20. The angle-of-attack range was -4° to 24°. Rolling, yawing, and pitching moments, and lift and drag were obtained with spoiler alone, spoiler-gap lip combination, and spoiler-slot deflector combination.
The spoiler used as a lateral-control device has been the subject of considerable investigation at low and high speeds, and on both swept and unswept wings (refs. 1 to 3). Recent investigations of spoilers used as lateral-control devices have shown that on thin wings with small leading-edge radii the unvented spoiler loses effectiveness rapidly as the angle of attack is increased above 8° (refs. 2 and 3). However, investigations at low and high subsonic speeds as reported in references 3 to 5 have shown that this loss in effectiveness at the higher angles of attack could be substantially reduced by using a slot in the wing behind the spoiler that would allow the air to flow through the wing from the lower to the upper surface when the spoiler was deflected.
The purpose of this investigation was to extend through the transonic speed range previous low and high subsonic speed investigations of spoiler-slut-deflector devices for lateral control. The investigation was made in the Langley high-speed 7- by 10-foot tunnel using the transonic bump to obtain Mach numbers from 0.62 to 1.20. The angle-of-attack range was -4° to 24°. Rolling, yawing, and pitching moments, and lift and drag were obtained with spoiler alone, spoiler-gap lip combination, and spoiler-slot deflector combination.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:11:35Z | |
| date available | 2017-09-04T15:11:35Z | |
| date copyright | 01/01/1953 | |
| date issued | 1953 | |
| identifier other | LUSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/10021 | |
| description abstract | INTRODUCTION The spoiler used as a lateral-control device has been the subject of considerable investigation at low and high speeds, and on both swept and unswept wings (refs. 1 to 3). Recent investigations of spoilers used as lateral-control devices have shown that on thin wings with small leading-edge radii the unvented spoiler loses effectiveness rapidly as the angle of attack is increased above 8° (refs. 2 and 3). However, investigations at low and high subsonic speeds as reported in references 3 to 5 have shown that this loss in effectiveness at the higher angles of attack could be substantially reduced by using a slot in the wing behind the spoiler that would allow the air to flow through the wing from the lower to the upper surface when the spoiler was deflected. The purpose of this investigation was to extend through the transonic speed range previous low and high subsonic speed investigations of spoiler-slut-deflector devices for lateral control. The investigation was made in the Langley high-speed 7- by 10-foot tunnel using the transonic bump to obtain Mach numbers from 0.62 to 1.20. The angle-of-attack range was -4° to 24°. Rolling, yawing, and pitching moments, and lift and drag were obtained with spoiler alone, spoiler-gap lip combination, and spoiler-slot deflector combination. | |
| language | English | |
| title | NACA-RM-L53J21 | num |
| title | Wind-tunnel investigation at transonic speeds of a spoiler-slot-deflector combination on an unswept NACA 65A006 wing | en |
| type | standard | |
| page | 29 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1953 | |
| contenttype | fulltext |