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NACA-TN-472
The effect of partial-span split flaps on the aerodynamic characteristics of a Clark Y wing
Year: 1933
Abstract: INTRODUCTION
Among the devices for increasing the maximum lift and also the drag of an airplane to improve the landing characteristics, is the split trailing-edge flap. With this arrangement the rear portion of the wing is split. into upper and lower sections and the lower section is deflected downward as a flap. This type of flap is designed for use over the maximum possible length of the wing span, no portion of the flap serving for lateral~ control.
Some tests have previously been made on airfoils with split flaps (references 1, 2, 3, and 4) in which the effects of changes in flap chord and deflection have been investigated The present investigation was made to determine the effects of changes in flap length and location along the wing span. The flaps were tested on a Clark Y wing in the 7 by 10 foot wind tunnel, and lift, drags, and pitching moment were measured for each size and location of flap. Only split flaps with a chord 20 percent of the wing chord were used since previous investigations indicated that flaps of this chord size would give results of most general value.
Among the devices for increasing the maximum lift and also the drag of an airplane to improve the landing characteristics, is the split trailing-edge flap. With this arrangement the rear portion of the wing is split. into upper and lower sections and the lower section is deflected downward as a flap. This type of flap is designed for use over the maximum possible length of the wing span, no portion of the flap serving for lateral~ control.
Some tests have previously been made on airfoils with split flaps (references 1, 2, 3, and 4) in which the effects of changes in flap chord and deflection have been investigated The present investigation was made to determine the effects of changes in flap length and location along the wing span. The flaps were tested on a Clark Y wing in the 7 by 10 foot wind tunnel, and lift, drags, and pitching moment were measured for each size and location of flap. Only split flaps with a chord 20 percent of the wing chord were used since previous investigations indicated that flaps of this chord size would give results of most general value.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:53:59Z | |
| date available | 2017-09-04T17:53:59Z | |
| date copyright | 01/01/1933 | |
| date issued | 1933 | |
| identifier other | FFYIYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/177124 | |
| description abstract | INTRODUCTION Among the devices for increasing the maximum lift and also the drag of an airplane to improve the landing characteristics, is the split trailing-edge flap. With this arrangement the rear portion of the wing is split. into upper and lower sections and the lower section is deflected downward as a flap. This type of flap is designed for use over the maximum possible length of the wing span, no portion of the flap serving for lateral~ control. Some tests have previously been made on airfoils with split flaps (references 1, 2, 3, and 4) in which the effects of changes in flap chord and deflection have been investigated The present investigation was made to determine the effects of changes in flap length and location along the wing span. The flaps were tested on a Clark Y wing in the 7 by 10 foot wind tunnel, and lift, drags, and pitching moment were measured for each size and location of flap. Only split flaps with a chord 20 percent of the wing chord were used since previous investigations indicated that flaps of this chord size would give results of most general value. | |
| language | English | |
| title | NACA-TN-472 | num |
| title | The effect of partial-span split flaps on the aerodynamic characteristics of a Clark Y wing | en |
| type | standard | |
| page | 10 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1933 | |
| contenttype | fulltext |