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NACA-TN-3007
Lift and pitching moment at low speeds of the naca 64A010 airfoil section equipped with various combinations of a leading-edge slat, leading-edge flap, split flap, and double-slotted flap
Year: 1953
Abstract: A two-dimensional wind-tunnel investigation at low speeds was made of the NACA 64A010 airfoil equipped with various combinations of a leading-edge slat, leading-edge flap, split flap, and double-slotted flap. Optimum slat positions were determined for a Reynolds number of 6million for the model with no trailing-edge flap and with the two trailing-edge flaps deflected. Section lift and pitching-moment characteristics of the various model arrangements were ascertained for Reynolds numbers of 2, 4, 6, and 7 million.
The increases in the maximum section lift coefficient produced by the leading-edge flap or by the leading-edge slat in combination with either of the trailing-edge flaps were approximately equal to the sum of the increments produced by each of the high-lift devices deflected individually. Extension of the leading-edge slat and deflection of the leading-edge flap produced increments in of about 0.83 and 0.66, respectively. Deflection of either leading-edge high-lift device caused the aerodynamic center to move forward. In the case of the leading-edge slat, the aerodynamic center moved forward to approximately the quarter point of the extended chord.
The increases in the maximum section lift coefficient produced by the leading-edge flap or by the leading-edge slat in combination with either of the trailing-edge flaps were approximately equal to the sum of the increments produced by each of the high-lift devices deflected individually. Extension of the leading-edge slat and deflection of the leading-edge flap produced increments in of about 0.83 and 0.66, respectively. Deflection of either leading-edge high-lift device caused the aerodynamic center to move forward. In the case of the leading-edge slat, the aerodynamic center moved forward to approximately the quarter point of the extended chord.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:10:52Z | |
| date available | 2017-09-04T15:10:52Z | |
| date copyright | 01/01/1953 | |
| date issued | 1953 | |
| identifier other | LSNUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/9214 | |
| description abstract | A two-dimensional wind-tunnel investigation at low speeds was made of the NACA 64A010 airfoil equipped with various combinations of a leading-edge slat, leading-edge flap, split flap, and double-slotted flap. Optimum slat positions were determined for a Reynolds number of 6million for the model with no trailing-edge flap and with the two trailing-edge flaps deflected. Section lift and pitching-moment characteristics of the various model arrangements were ascertained for Reynolds numbers of 2, 4, 6, and 7 million. The increases in the maximum section lift coefficient produced by the leading-edge flap or by the leading-edge slat in combination with either of the trailing-edge flaps were approximately equal to the sum of the increments produced by each of the high-lift devices deflected individually. Extension of the leading-edge slat and deflection of the leading-edge flap produced increments in of about 0.83 and 0.66, respectively. Deflection of either leading-edge high-lift device caused the aerodynamic center to move forward. In the case of the leading-edge slat, the aerodynamic center moved forward to approximately the quarter point of the extended chord. | |
| language | English | |
| title | NACA-TN-3007 | num |
| title | Lift and pitching moment at low speeds of the naca 64A010 airfoil section equipped with various combinations of a leading-edge slat, leading-edge flap, split flap, and double-slotted flap | en |
| type | standard | |
| page | 46 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1953 | |
| contenttype | fulltext |