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NACA-WR-L-464
Wind-tunnel investigation of control-surface characteristics V - the use of a beveled trailing edge to reduce the hinge moment of a control surface
Year: 1942
Abstract: Wind-tunnel tests have been made to investigate the possibility of reducing the hinge moments of a control surface by beveling the trailing edge. The tests were made with a 9-percent-thick airfoil having a 30-percent-chord plain flap. A faired beveled shape, 5 percent of the airfoil chord in width and having a thickness of 2½ percent of the airfoil chord, was found to give approximately 50- percent reduction in the hinge moment caused by a given deflection of the flap and 80-percent reduction in the hinge moment due to the angle of attack of this airfoil for a wide range of angle. A blunter beveled portion of the same thickness gave overbalance and reversal of the floating tendency over a small angular range. Elliptical trailing-edge shapes were also tried but were found to be somewhat less effective than the shapes ending in an acute angle. A semicircular trailing edge produced only a slight change in the hinge moments but caused a drag increment much greater than that of an efficient beveled shape.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:28:06Z | |
| date available | 2017-09-04T16:28:06Z | |
| date copyright | 01/01/1942 | |
| date issued | 1942 | |
| identifier other | UEYYYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/91293 | |
| description abstract | Wind-tunnel tests have been made to investigate the possibility of reducing the hinge moments of a control surface by beveling the trailing edge. The tests were made with a 9-percent-thick airfoil having a 30-percent-chord plain flap. A faired beveled shape, 5 percent of the airfoil chord in width and having a thickness of 2½ percent of the airfoil chord, was found to give approximately 50- percent reduction in the hinge moment caused by a given deflection of the flap and 80-percent reduction in the hinge moment due to the angle of attack of this airfoil for a wide range of angle. A blunter beveled portion of the same thickness gave overbalance and reversal of the floating tendency over a small angular range. Elliptical trailing-edge shapes were also tried but were found to be somewhat less effective than the shapes ending in an acute angle. A semicircular trailing edge produced only a slight change in the hinge moments but caused a drag increment much greater than that of an efficient beveled shape. | |
| language | English | |
| title | NACA-WR-L-464 | num |
| title | Wind-tunnel investigation of control-surface characteristics V - the use of a beveled trailing edge to reduce the hinge moment of a control surface | en |
| type | standard | |
| page | 24 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1942 | |
| contenttype | fulltext |