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NACA-RM-L50J20
Low-speed investigation of the effect of several flap and spoiler ailerons on the lateral characteristics of a 47.5 degrees sweptback-wing-fuselage combination at a Reynolds number of 4.4. x 10(6)
Year: 1950
Abstract: INTRODUCTION
Lateral-control devices &Signed for airplanes flying at high speeds may produce unsatisfactory lateral characteristics at the lower flight speeds. Much research has been made t o investigate the lateral characteristics of swept and -wept wings and low-aspect-ratio and high-aspect ratio wings equipped with several types of lateral-control devices (references 1 to 4 and unpublished results). In order to supplement further the data of the above references, an investigation has been made at a high Reynolds number in the Langley fill-scale tunnel on a 47.5° sweptback wing having an aspect ratio of 3.4 and a taper ratio of 0.51.
The data presented herein include test results of a 19-percent-chord plain-flap aileron having various spans and trailing-edge thicknesses. The effects of spoiler spanwise and chordwise location and projection on the lateral characteristics of the model are also shown. The results are presented for the basic wing and the wing with extensible leading-edge and plain trailing-edge flaps through a range of angles of attack from small negative angles through maximum lift at a Reynolds number of approximately 4.4. X 106 and a Mach number of 0.07.
Lateral-control devices &Signed for airplanes flying at high speeds may produce unsatisfactory lateral characteristics at the lower flight speeds. Much research has been made t o investigate the lateral characteristics of swept and -wept wings and low-aspect-ratio and high-aspect ratio wings equipped with several types of lateral-control devices (references 1 to 4 and unpublished results). In order to supplement further the data of the above references, an investigation has been made at a high Reynolds number in the Langley fill-scale tunnel on a 47.5° sweptback wing having an aspect ratio of 3.4 and a taper ratio of 0.51.
The data presented herein include test results of a 19-percent-chord plain-flap aileron having various spans and trailing-edge thicknesses. The effects of spoiler spanwise and chordwise location and projection on the lateral characteristics of the model are also shown. The results are presented for the basic wing and the wing with extensible leading-edge and plain trailing-edge flaps through a range of angles of attack from small negative angles through maximum lift at a Reynolds number of approximately 4.4. X 106 and a Mach number of 0.07.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:15:58Z | |
| date available | 2017-09-04T16:15:58Z | |
| date copyright | 01/01/1950 | |
| date issued | 1950 | |
| identifier other | BKSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/79290 | |
| description abstract | INTRODUCTION Lateral-control devices &Signed for airplanes flying at high speeds may produce unsatisfactory lateral characteristics at the lower flight speeds. Much research has been made t o investigate the lateral characteristics of swept and -wept wings and low-aspect-ratio and high-aspect ratio wings equipped with several types of lateral-control devices (references 1 to 4 and unpublished results). In order to supplement further the data of the above references, an investigation has been made at a high Reynolds number in the Langley fill-scale tunnel on a 47.5° sweptback wing having an aspect ratio of 3.4 and a taper ratio of 0.51. The data presented herein include test results of a 19-percent-chord plain-flap aileron having various spans and trailing-edge thicknesses. The effects of spoiler spanwise and chordwise location and projection on the lateral characteristics of the model are also shown. The results are presented for the basic wing and the wing with extensible leading-edge and plain trailing-edge flaps through a range of angles of attack from small negative angles through maximum lift at a Reynolds number of approximately 4.4. X 106 and a Mach number of 0.07. | |
| language | English | |
| title | NACA-RM-L50J20 | num |
| title | Low-speed investigation of the effect of several flap and spoiler ailerons on the lateral characteristics of a 47.5 degrees sweptback-wing-fuselage combination at a Reynolds number of 4.4. x 10(6) | en |
| type | standard | |
| page | 59 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1950 | |
| contenttype | fulltext |