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NACA-TR-634
Calculation of the chordwise load distribution over airfoil sections with plain, split, or serially hinged trailing-edge flaps
Year: 1938
Abstract: A method is presented for the rapid calculation of the incremental chordwise normal-force distribution over an airfoil section due to the deflection of a plain flap or tab, a split flap, or a serially hinged flap. This report is intended as a supplement to NACA Report no. 631, wherein a method is presented for the calculation of the chordwise normal-force distribution over an airfoil without a flap or, as it may be considered, an airfoil with flap (or flaps) neutral. The method enables the determination of the form and magnitude of the incremental normal-force distribution to be made for an airfoil-flap combination for which the section characteristics have been determined. A method is included for the calculation of the flap normal-force and hinge-moment coefficients without necessitating a determination of the normal-force distribution.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:11:58Z | |
| date available | 2017-09-04T17:11:58Z | |
| date copyright | 01/01/1938 | |
| date issued | 1938 | |
| identifier other | YTWUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/135471 | |
| description abstract | A method is presented for the rapid calculation of the incremental chordwise normal-force distribution over an airfoil section due to the deflection of a plain flap or tab, a split flap, or a serially hinged flap. This report is intended as a supplement to NACA Report no. 631, wherein a method is presented for the calculation of the chordwise normal-force distribution over an airfoil without a flap or, as it may be considered, an airfoil with flap (or flaps) neutral. The method enables the determination of the form and magnitude of the incremental normal-force distribution to be made for an airfoil-flap combination for which the section characteristics have been determined. A method is included for the calculation of the flap normal-force and hinge-moment coefficients without necessitating a determination of the normal-force distribution. | |
| language | English | |
| title | NACA-TR-634 | num |
| title | Calculation of the chordwise load distribution over airfoil sections with plain, split, or serially hinged trailing-edge flaps | en |
| type | standard | |
| page | 24 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1938 | |
| contenttype | fulltext |