درباره ما
NACA-RM-L57C20
Results of an investigation at high subsonic speeds to determine lateral-control and hinge-moment characteristics of a spoiler-slot-deflector configuration on a 35 degrees sweptback wing
Year: 1957
Abstract: INTRODUCTION
Recent investigations of spoiler-type controls suitable for use on high-speed thin-wing configurations have shown that the spoiler slot deflector has certain advantages over the plain flap-type spoiler, such as lower hinge moments and more effectiveness at high angles of attack (for example, ref. 1).
The spoiler and deflector of a spoiler-slot-deflector configuration designed for an airplane installation would in all probability be constructed of box-type sections withstand the loads imposed on the control in flight. The spoiler and deflector should be designed to maintain good flow properties through the slot of the control.
In order to determine the lateral-control hinge-moment characteristics of one such box-type spoiler and deflector configuration, an investigation was made in the Langley high 7- by 10-foot tunnel of an inboard 41-percent-semispan spoiler slot deflector on a 35° sweptback-semispan-wing model.
The spoiler and deflector had chord of 15 percent of the wing chord and were hinged along the 55-percent and 70-percent-chord line, respectively; thus tests could be made on the spoiler-slot-deflector configuration at various control projection
Recent investigations of spoiler-type controls suitable for use on high-speed thin-wing configurations have shown that the spoiler slot deflector has certain advantages over the plain flap-type spoiler, such as lower hinge moments and more effectiveness at high angles of attack (for example, ref. 1).
The spoiler and deflector of a spoiler-slot-deflector configuration designed for an airplane installation would in all probability be constructed of box-type sections withstand the loads imposed on the control in flight. The spoiler and deflector should be designed to maintain good flow properties through the slot of the control.
In order to determine the lateral-control hinge-moment characteristics of one such box-type spoiler and deflector configuration, an investigation was made in the Langley high 7- by 10-foot tunnel of an inboard 41-percent-semispan spoiler slot deflector on a 35° sweptback-semispan-wing model.
The spoiler and deflector had chord of 15 percent of the wing chord and were hinged along the 55-percent and 70-percent-chord line, respectively; thus tests could be made on the spoiler-slot-deflector configuration at various control projection
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:48:43Z | |
| date available | 2017-09-04T15:48:43Z | |
| date copyright | 01/01/1957 | |
| date issued | 1957 | |
| identifier other | QBYIYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/51663 | |
| description abstract | INTRODUCTION Recent investigations of spoiler-type controls suitable for use on high-speed thin-wing configurations have shown that the spoiler slot deflector has certain advantages over the plain flap-type spoiler, such as lower hinge moments and more effectiveness at high angles of attack (for example, ref. 1). The spoiler and deflector of a spoiler-slot-deflector configuration designed for an airplane installation would in all probability be constructed of box-type sections withstand the loads imposed on the control in flight. The spoiler and deflector should be designed to maintain good flow properties through the slot of the control. In order to determine the lateral-control hinge-moment characteristics of one such box-type spoiler and deflector configuration, an investigation was made in the Langley high 7- by 10-foot tunnel of an inboard 41-percent-semispan spoiler slot deflector on a 35° sweptback-semispan-wing model. The spoiler and deflector had chord of 15 percent of the wing chord and were hinged along the 55-percent and 70-percent-chord line, respectively; thus tests could be made on the spoiler-slot-deflector configuration at various control projection | |
| language | English | |
| title | NACA-RM-L57C20 | num |
| title | Results of an investigation at high subsonic speeds to determine lateral-control and hinge-moment characteristics of a spoiler-slot-deflector configuration on a 35 degrees sweptback wing | en |
| type | standard | |
| page | 82 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1957 | |
| contenttype | fulltext |