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NACA-TN-3497
Summary of results of a wind-tunnel investigation of nine related horizontal tails
Year: 1955
Abstract: The results of a wind-tunnel investigation of a series of models of nine related horizontal tails have been summarized to provide basic design information; to indicate the effects of aspect ratio, sweepback, and changes in the Mach number; and to provide experimental values of the lift and hinge-moment parameters for comparison with values computed by a method employing lifting-surface theory. The models had aspect ratios from 2 to 6, angles of sweepback of the quarter-chord line from 5.7° to 45°, a taper ratio of 0.5, and had 30-percent-chord, sealed, plain flaps. The Mach number was varied from 0.12 to 0.94 for Reynolds numbers of 2, 3, or 4 million. Also, a constant-chord airfoil having the NACA 64A010 section and completely spanning the wind tunnel was tested at a Mach number of 0.12. This airfoil had the same section and flap-chord ratio as the nine horizontal-tail models.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:11:52Z | |
| date available | 2017-09-04T15:11:52Z | |
| date copyright | 01/01/1955 | |
| date issued | 1955 | |
| identifier other | LVNUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/10296 | |
| description abstract | The results of a wind-tunnel investigation of a series of models of nine related horizontal tails have been summarized to provide basic design information; to indicate the effects of aspect ratio, sweepback, and changes in the Mach number; and to provide experimental values of the lift and hinge-moment parameters for comparison with values computed by a method employing lifting-surface theory. The models had aspect ratios from 2 to 6, angles of sweepback of the quarter-chord line from 5.7° to 45°, a taper ratio of 0.5, and had 30-percent-chord, sealed, plain flaps. The Mach number was varied from 0.12 to 0.94 for Reynolds numbers of 2, 3, or 4 million. Also, a constant-chord airfoil having the NACA 64A010 section and completely spanning the wind tunnel was tested at a Mach number of 0.12. This airfoil had the same section and flap-chord ratio as the nine horizontal-tail models. | |
| language | English | |
| title | NACA-TN-3497 | num |
| title | Summary of results of a wind-tunnel investigation of nine related horizontal tails | en |
| type | standard | |
| page | 106 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1955 | |
| contenttype | fulltext |