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NACA-RM-A51D02
Investigation in the Ames 12-foot pressure wind tunnel of a model horizontal tail of aspect ratio 3 and taper ratio 0.5 having the quarter-chord line swept back 45 degrees
Year: 1951
Abstract: INTRODUCTION
A systematic investigation has been undertaken at the Ames Aeronautical Laboratory to determine the effects of plan form on the control-effectiveness and the hinge-moment parameters of horizontal tails having full-span trailing-edge flaps. References 1 through 7 present results of wind-tunnel tests of both swept and unswept horizontal tails of several aspect ratios, all having the same taper ratio and airfoil section as the subject model.
As a part of this investigation the tests reported herein were conducted to evaluate the effects of compressibility and of Reynolds number on the control-surface characteristic of a horizontal tail having 45 of sweepback. Since this model also represents a wing with a full-span flap, drag and pitching-moment data are included in addition to the lift and hinge-moment data.
A systematic investigation has been undertaken at the Ames Aeronautical Laboratory to determine the effects of plan form on the control-effectiveness and the hinge-moment parameters of horizontal tails having full-span trailing-edge flaps. References 1 through 7 present results of wind-tunnel tests of both swept and unswept horizontal tails of several aspect ratios, all having the same taper ratio and airfoil section as the subject model.
As a part of this investigation the tests reported herein were conducted to evaluate the effects of compressibility and of Reynolds number on the control-surface characteristic of a horizontal tail having 45 of sweepback. Since this model also represents a wing with a full-span flap, drag and pitching-moment data are included in addition to the lift and hinge-moment data.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:36:08Z | |
| date available | 2017-09-04T18:36:08Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | JKMCWDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;query=authoCA5893FD081D49A96159DD6EFDEC014A/handle/yse/218127 | |
| description abstract | INTRODUCTION A systematic investigation has been undertaken at the Ames Aeronautical Laboratory to determine the effects of plan form on the control-effectiveness and the hinge-moment parameters of horizontal tails having full-span trailing-edge flaps. References 1 through 7 present results of wind-tunnel tests of both swept and unswept horizontal tails of several aspect ratios, all having the same taper ratio and airfoil section as the subject model. As a part of this investigation the tests reported herein were conducted to evaluate the effects of compressibility and of Reynolds number on the control-surface characteristic of a horizontal tail having 45 of sweepback. Since this model also represents a wing with a full-span flap, drag and pitching-moment data are included in addition to the lift and hinge-moment data. | |
| language | English | |
| title | NACA-RM-A51D02 | num |
| title | Investigation in the Ames 12-foot pressure wind tunnel of a model horizontal tail of aspect ratio 3 and taper ratio 0.5 having the quarter-chord line swept back 45 degrees | en |
| type | standard | |
| page | 99 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext |