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NACA-RM-L9D06
Wing-tunnel investigation at high subsonic speeds of the lateral-control characteristics of an aileron and a stepped spoiler on a wing with leading edge swept back 51.3 degrees
Year: 1949
Abstract: INTRODUCTION
The importance of obtaining adequate lateral control for airplanes incorporating sweptback wings has led the NACA to engage in an extensive program of lateral-control research on various sweptback-wing configurations. The purposes of this program are to determine the characteristics of various lateral-control devices, to attempt to improve these characteristics where possible by modification of these-devices, and to investigate wholly new lateral-control devices.
Reported herein are the results of a lateral-control investigation of a 20-percent-chord by 39-percent-semispan sealed plain aileron on a 51.3° sweptback wing having an aspect ratio of 3.06 and a taper ratio of 0.49. The lateral-control characteristics of two stepped spoilers, similar t o spoiler 18 of reference 1, were also investigated.
Aileron rolling-moment, yawing-moment, and hinge-moment coefficients wore determined through a speed range from a Mack number of 0.30 t o a Mach number of 0.91 over a range of aileron deflection of approximately +30°and a range of wing angle of attack from approximately -4° to 16°. Spoiler rolling-moment and yawing-moment coefficient were determined for both spoiler configurations at one spoiler projection through the speed range and at wing angles of attack from approximately -4° to 4°. The characteristics of the more satisfactory of the two spoiler configurations were determined through a range of spoiler projection.
The tests were made in the Langley high-speed 7- by 10-foot tunnel.
The importance of obtaining adequate lateral control for airplanes incorporating sweptback wings has led the NACA to engage in an extensive program of lateral-control research on various sweptback-wing configurations. The purposes of this program are to determine the characteristics of various lateral-control devices, to attempt to improve these characteristics where possible by modification of these-devices, and to investigate wholly new lateral-control devices.
Reported herein are the results of a lateral-control investigation of a 20-percent-chord by 39-percent-semispan sealed plain aileron on a 51.3° sweptback wing having an aspect ratio of 3.06 and a taper ratio of 0.49. The lateral-control characteristics of two stepped spoilers, similar t o spoiler 18 of reference 1, were also investigated.
Aileron rolling-moment, yawing-moment, and hinge-moment coefficients wore determined through a speed range from a Mack number of 0.30 t o a Mach number of 0.91 over a range of aileron deflection of approximately +30°and a range of wing angle of attack from approximately -4° to 16°. Spoiler rolling-moment and yawing-moment coefficient were determined for both spoiler configurations at one spoiler projection through the speed range and at wing angles of attack from approximately -4° to 4°. The characteristics of the more satisfactory of the two spoiler configurations were determined through a range of spoiler projection.
The tests were made in the Langley high-speed 7- by 10-foot tunnel.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:33:11Z | |
| date available | 2017-09-04T15:33:11Z | |
| date copyright | 01/01/1949 | |
| date issued | 1949 | |
| identifier other | OISWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/34747 | |
| description abstract | INTRODUCTION The importance of obtaining adequate lateral control for airplanes incorporating sweptback wings has led the NACA to engage in an extensive program of lateral-control research on various sweptback-wing configurations. The purposes of this program are to determine the characteristics of various lateral-control devices, to attempt to improve these characteristics where possible by modification of these-devices, and to investigate wholly new lateral-control devices. Reported herein are the results of a lateral-control investigation of a 20-percent-chord by 39-percent-semispan sealed plain aileron on a 51.3° sweptback wing having an aspect ratio of 3.06 and a taper ratio of 0.49. The lateral-control characteristics of two stepped spoilers, similar t o spoiler 18 of reference 1, were also investigated. Aileron rolling-moment, yawing-moment, and hinge-moment coefficients wore determined through a speed range from a Mack number of 0.30 t o a Mach number of 0.91 over a range of aileron deflection of approximately +30°and a range of wing angle of attack from approximately -4° to 16°. Spoiler rolling-moment and yawing-moment coefficient were determined for both spoiler configurations at one spoiler projection through the speed range and at wing angles of attack from approximately -4° to 4°. The characteristics of the more satisfactory of the two spoiler configurations were determined through a range of spoiler projection. The tests were made in the Langley high-speed 7- by 10-foot tunnel. | |
| language | English | |
| title | NACA-RM-L9D06 | num |
| title | Wing-tunnel investigation at high subsonic speeds of the lateral-control characteristics of an aileron and a stepped spoiler on a wing with leading edge swept back 51.3 degrees | en |
| type | standard | |
| page | 35 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1949 | |
| contenttype | fulltext |