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NACA-RM-L51L10
Wind-tunnel investigation at high subsonic speeds of spoilers of large projection on an NACA 65A006 wing with quarter-chord line swept back 32.6 degrees
Year: 1952
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 (references 1 to 7). Many of the advantages as well as some of the disadvantages of the spoiler have been discussed. Spoilers of various spans located at various spanwise and chordwise positions and skew angles have been tested in order to determine the more effective locations. Most of the wings used in these previous investigations were 10 percent thick or more, and the spoiler projections were limited to 10 percent or less of the wing chord.
The purpose of the investigation reported herein was to determine the rolling-moment effectiveness and other aerodynamic characteristics of spoilers of projections greater than 10 percent chord on a 6-percent-thick sweptback wing. This investigation was conducted in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.4 t o 0.91 and an angle-of-attack range from 0° to 24° except when limited by tunnel operating conditions. Lift, drag, rolling, pitching, and yawing moments were obtained with spoiler projections 8s great as 25 percent of the local wing chord.
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 (references 1 to 7). Many of the advantages as well as some of the disadvantages of the spoiler have been discussed. Spoilers of various spans located at various spanwise and chordwise positions and skew angles have been tested in order to determine the more effective locations. Most of the wings used in these previous investigations were 10 percent thick or more, and the spoiler projections were limited to 10 percent or less of the wing chord.
The purpose of the investigation reported herein was to determine the rolling-moment effectiveness and other aerodynamic characteristics of spoilers of projections greater than 10 percent chord on a 6-percent-thick sweptback wing. This investigation was conducted in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.4 t o 0.91 and an angle-of-attack range from 0° to 24° except when limited by tunnel operating conditions. Lift, drag, rolling, pitching, and yawing moments were obtained with spoiler projections 8s great as 25 percent of the local wing chord.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:01:42Z | |
| date available | 2017-09-04T16:01:42Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | RLSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/64907 | |
| 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 (references 1 to 7). Many of the advantages as well as some of the disadvantages of the spoiler have been discussed. Spoilers of various spans located at various spanwise and chordwise positions and skew angles have been tested in order to determine the more effective locations. Most of the wings used in these previous investigations were 10 percent thick or more, and the spoiler projections were limited to 10 percent or less of the wing chord. The purpose of the investigation reported herein was to determine the rolling-moment effectiveness and other aerodynamic characteristics of spoilers of projections greater than 10 percent chord on a 6-percent-thick sweptback wing. This investigation was conducted in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.4 t o 0.91 and an angle-of-attack range from 0° to 24° except when limited by tunnel operating conditions. Lift, drag, rolling, pitching, and yawing moments were obtained with spoiler projections 8s great as 25 percent of the local wing chord. | |
| language | English | |
| title | NACA-RM-L51L10 | num |
| title | Wind-tunnel investigation at high subsonic speeds of spoilers of large projection on an NACA 65A006 wing with quarter-chord line swept back 32.6 degrees | en |
| type | standard | |
| page | 33 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |