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NACA-TN-4040
Estimation of incremental pitching moments due to trailing-edge flaps on swept and triangular wings
Year: 1957
Abstract: A method is presented whereby incremental pitching moments can be estimated for swept and triangular wings having arbitrary types of trailing-edge high-lift flaps. In the method use is made of span-loading theory together with two-dimensional airfoil data adjusted for the effects of sweep. The method as presented was limited to low speeds and small angles of attack.
Application of the method is demonstrated for some 58 cases covering various types of flaps on wings having a wide range of sweep, aspect ratio, and taper ratio. For all wings, swept as well as triangular, a mean derivation from experiment of about 0.02 in incremental pitching-moment coefficient was found.
Application of the method is demonstrated for some 58 cases covering various types of flaps on wings having a wide range of sweep, aspect ratio, and taper ratio. For all wings, swept as well as triangular, a mean derivation from experiment of about 0.02 in incremental pitching-moment coefficient was found.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:13:58Z | |
| date available | 2017-09-04T17:13:58Z | |
| date copyright | 01/01/1957 | |
| date issued | 1957 | |
| identifier other | YZNUYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/137448 | |
| description abstract | A method is presented whereby incremental pitching moments can be estimated for swept and triangular wings having arbitrary types of trailing-edge high-lift flaps. In the method use is made of span-loading theory together with two-dimensional airfoil data adjusted for the effects of sweep. The method as presented was limited to low speeds and small angles of attack. Application of the method is demonstrated for some 58 cases covering various types of flaps on wings having a wide range of sweep, aspect ratio, and taper ratio. For all wings, swept as well as triangular, a mean derivation from experiment of about 0.02 in incremental pitching-moment coefficient was found. | |
| language | English | |
| title | NACA-TN-4040 | num |
| title | Estimation of incremental pitching moments due to trailing-edge flaps on swept and triangular wings | en |
| type | standard | |
| page | 32 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1957 | |
| contenttype | fulltext |