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NACA-TN-1624
Two-dimensional wind-tunnel investigation of an NACA 64-009 airfoil equipped with two types of leading-edge flap
Year: 1948
Abstract: An investigation was made to determine the effect of leading-edge flaps on the maximum lift coefficient of an NACA 64-009 airfoil and to compare the results with data obtained from previous tests of similarly shaped flaps on an NACA 641-012 airfoil (NACA TN No. 1277). The investigation included tests of two 10-percent-chord leading-edge flaps, one intended to slide forward along the upper surface and the other hinged at the center of the airfoil leading-edge radius and deflecting from the lower surface. The flaps were tested on the plain airfoil and on the airfoil with a trailing-edge split flap deflected 60º. Data are given to show the section lift characteristics for a range of flap deflection and the section pitching-moment and lift characteristics with leading-edge roughness for the optimum flap arrangements.
Subject: AIRFOILS
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:51:04Z | |
| date available | 2017-09-04T17:51:04Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | EYQTYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/174376 | |
| description abstract | An investigation was made to determine the effect of leading-edge flaps on the maximum lift coefficient of an NACA 64-009 airfoil and to compare the results with data obtained from previous tests of similarly shaped flaps on an NACA 641-012 airfoil (NACA TN No. 1277). The investigation included tests of two 10-percent-chord leading-edge flaps, one intended to slide forward along the upper surface and the other hinged at the center of the airfoil leading-edge radius and deflecting from the lower surface. The flaps were tested on the plain airfoil and on the airfoil with a trailing-edge split flap deflected 60º. Data are given to show the section lift characteristics for a range of flap deflection and the section pitching-moment and lift characteristics with leading-edge roughness for the optimum flap arrangements. | |
| language | English | |
| title | NACA-TN-1624 | num |
| title | Two-dimensional wind-tunnel investigation of an NACA 64-009 airfoil equipped with two types of leading-edge flap | en |
| type | standard | |
| page | 31 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext | |
| subject keywords | AIRFOILS | |
| subject keywords | CARRIED | |
| subject keywords | CHAR | |
| subject keywords | CHARACTERISTICS | |
| subject keywords | DRAG | |
| subject keywords | EDGE | |
| subject keywords | EFFECT | |
| subject keywords | FLAPS | |
| subject keywords | LEADING | |
| subject keywords | LOW | |
| subject keywords | MOMENTS | |
| subject keywords | NACA | |
| subject keywords | ORDINATES | |
| subject keywords | PRESSURE | |
| subject keywords | ROUGHNESS | |
| subject keywords | SPLIT | |
| subject keywords | SURFACE | |
| subject keywords | TESTS | |
| subject keywords | TUNNEL | |
| subject keywords | TURBULENCE | |
| subject keywords | WIND | |
| subject keywords | WING | |
| subject keywords | WORK |