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NACA-RM-L53D17
Wind-tunnel investigation at high subsonic speeds of a spoiler-slot-deflector combination on an NACA 65A006 wing with quarter-chord line swept back 32.6 degrees
Year: 1953
Abstract: INTRODUCTION
The spoiler used as a lateral-control device has been the subjected of considerable investigation at low and high speeds, and on both swept and unswept wings. Recent investigations of spoilers used as lateral-control devices have shown that on this wings with small leading-edge radii the unvented spoiler loses effectiveness rapidly as the angle of attack is increased above about 8º (ref. 1). References 2 and 3 have shown that this loss in effectiveness at the higher angles of attack could be reduced by using a slot in the wing behind angles of attack could be reduced by using a slot in the wing behind the spoiler that allowed 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 determine whether a slot plus a deflector is as effective at high subsonic speeds as it was at low speeds (refs. 2 and 4), and if so, to determine the ratio of deflector projection to spoiler projection for most beneficial results. The investigation was conducted in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.4 to 0.94 and at an angle-of-attack range from 0º to 20º except when limited by tunnel operating conditions. Rolling and yawing moments were obtained with spoiler alone, with slot plus deflector, and with spoiler-slot-deflector combination. Lift, drag, and pitching moments of the model were also obtained for the spoiler-slot-deflector combination.
The spoiler used as a lateral-control device has been the subjected of considerable investigation at low and high speeds, and on both swept and unswept wings. Recent investigations of spoilers used as lateral-control devices have shown that on this wings with small leading-edge radii the unvented spoiler loses effectiveness rapidly as the angle of attack is increased above about 8º (ref. 1). References 2 and 3 have shown that this loss in effectiveness at the higher angles of attack could be reduced by using a slot in the wing behind angles of attack could be reduced by using a slot in the wing behind the spoiler that allowed 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 determine whether a slot plus a deflector is as effective at high subsonic speeds as it was at low speeds (refs. 2 and 4), and if so, to determine the ratio of deflector projection to spoiler projection for most beneficial results. The investigation was conducted in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.4 to 0.94 and at an angle-of-attack range from 0º to 20º except when limited by tunnel operating conditions. Rolling and yawing moments were obtained with spoiler alone, with slot plus deflector, and with spoiler-slot-deflector combination. Lift, drag, and pitching moments of the model were also obtained for the spoiler-slot-deflector combination.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:21:31Z | |
| date available | 2017-09-04T16:21:31Z | |
| date copyright | 01/01/1953 | |
| date issued | 1953 | |
| identifier other | TNSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/84958 | |
| description abstract | INTRODUCTION The spoiler used as a lateral-control device has been the subjected of considerable investigation at low and high speeds, and on both swept and unswept wings. Recent investigations of spoilers used as lateral-control devices have shown that on this wings with small leading-edge radii the unvented spoiler loses effectiveness rapidly as the angle of attack is increased above about 8º (ref. 1). References 2 and 3 have shown that this loss in effectiveness at the higher angles of attack could be reduced by using a slot in the wing behind angles of attack could be reduced by using a slot in the wing behind the spoiler that allowed 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 determine whether a slot plus a deflector is as effective at high subsonic speeds as it was at low speeds (refs. 2 and 4), and if so, to determine the ratio of deflector projection to spoiler projection for most beneficial results. The investigation was conducted in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.4 to 0.94 and at an angle-of-attack range from 0º to 20º except when limited by tunnel operating conditions. Rolling and yawing moments were obtained with spoiler alone, with slot plus deflector, and with spoiler-slot-deflector combination. Lift, drag, and pitching moments of the model were also obtained for the spoiler-slot-deflector combination. | |
| language | English | |
| title | NACA-RM-L53D17 | num |
| title | Wind-tunnel investigation at high subsonic speeds of a spoiler-slot-deflector combination on an NACA 65A006 wing with quarter-chord line swept back 32.6 degrees | en |
| type | standard | |
| page | 25 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1953 | |
| contenttype | fulltext |