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NACA-RM-L51A26
Investigation at low speed of the effectiveness and hinge moments of a constant-chord elevator on a large-scale triangular wing with section modification
Year: 1951
Abstract: INTRODUCTION
Previous pressure-distribution and flow investigations of triangular wings (references 1, 2, and 3) have shown leading-edge separation with an accompanying strong vortex flow for wings with sharp-edged airfoils, but the effect of the vortex decreased for the wings having airfoil sections with increasing nose redial. In fact, the large-scale trim angular wing of reference 1 and the small-scale triangular wing of reference 4, both with rounded leading edges, showed training-edge separation of the type normally expected for conventional wings.
In the flow investigation of a zero-taper-ratio wing, reported in reference 3, it was shown that the separation vortices increased in size and intensity as they swept progressively form the leading edge inboard toward the plane of symmetry with increased angle of attack. The progression of this type of flow over the tip sections and wing trailing edge would be expected to influence the control characteristics of trailing-edge flaps or ailavators, in view of the varied loading of the sections.
The present tests were conducted into eh Langley full-scale tunnel to investigate the effects of the vortex flow on the effectiveness and hinge-moment characteristics of outboard, inboard, and full-semi span constant-chord ailavators on the large-scale triangular wing of reference 5.
In an attempt to alleviate the leading-edge separation and vortex flow, the nose section of the basic wing was altered by installing a glove incorporating NACA 65-010 section ordinates parallel to the free stream over the forward 10 percent of the chord and faired to the wing at approximately the 50-percent-chord line.
Previous pressure-distribution and flow investigations of triangular wings (references 1, 2, and 3) have shown leading-edge separation with an accompanying strong vortex flow for wings with sharp-edged airfoils, but the effect of the vortex decreased for the wings having airfoil sections with increasing nose redial. In fact, the large-scale trim angular wing of reference 1 and the small-scale triangular wing of reference 4, both with rounded leading edges, showed training-edge separation of the type normally expected for conventional wings.
In the flow investigation of a zero-taper-ratio wing, reported in reference 3, it was shown that the separation vortices increased in size and intensity as they swept progressively form the leading edge inboard toward the plane of symmetry with increased angle of attack. The progression of this type of flow over the tip sections and wing trailing edge would be expected to influence the control characteristics of trailing-edge flaps or ailavators, in view of the varied loading of the sections.
The present tests were conducted into eh Langley full-scale tunnel to investigate the effects of the vortex flow on the effectiveness and hinge-moment characteristics of outboard, inboard, and full-semi span constant-chord ailavators on the large-scale triangular wing of reference 5.
In an attempt to alleviate the leading-edge separation and vortex flow, the nose section of the basic wing was altered by installing a glove incorporating NACA 65-010 section ordinates parallel to the free stream over the forward 10 percent of the chord and faired to the wing at approximately the 50-percent-chord line.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:20:25Z | |
| date available | 2017-09-04T16:20:25Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | TKSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/83842 | |
| description abstract | INTRODUCTION Previous pressure-distribution and flow investigations of triangular wings (references 1, 2, and 3) have shown leading-edge separation with an accompanying strong vortex flow for wings with sharp-edged airfoils, but the effect of the vortex decreased for the wings having airfoil sections with increasing nose redial. In fact, the large-scale trim angular wing of reference 1 and the small-scale triangular wing of reference 4, both with rounded leading edges, showed training-edge separation of the type normally expected for conventional wings. In the flow investigation of a zero-taper-ratio wing, reported in reference 3, it was shown that the separation vortices increased in size and intensity as they swept progressively form the leading edge inboard toward the plane of symmetry with increased angle of attack. The progression of this type of flow over the tip sections and wing trailing edge would be expected to influence the control characteristics of trailing-edge flaps or ailavators, in view of the varied loading of the sections. The present tests were conducted into eh Langley full-scale tunnel to investigate the effects of the vortex flow on the effectiveness and hinge-moment characteristics of outboard, inboard, and full-semi span constant-chord ailavators on the large-scale triangular wing of reference 5. In an attempt to alleviate the leading-edge separation and vortex flow, the nose section of the basic wing was altered by installing a glove incorporating NACA 65-010 section ordinates parallel to the free stream over the forward 10 percent of the chord and faired to the wing at approximately the 50-percent-chord line. | |
| language | English | |
| title | NACA-RM-L51A26 | num |
| title | Investigation at low speed of the effectiveness and hinge moments of a constant-chord elevator on a large-scale triangular wing with section modification | en |
| type | standard | |
| page | 49 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext |