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NACA-RM-L8K22
Two-dimensional wind-tunnel investigation of two NACA 6-series airfoils with leading-edge slats
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:28:13Z | |
| date available | 2017-09-04T15:28:13Z | |
| date copyright | 01/01/1949 | |
| date issued | 1949 | |
| identifier other | NTSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/29244 | |
| description abstract | INTRODUCTION Some of the problems encountered with the use of thin airfoils and sweep back on wings of high speed airplanes are low maximum lift and tip stalling. Previous investigations of airfoils of various thicknesses (references 1 to 4) indicate that leading-edge slats maintain installed flow over the airfoil up to angles of attack greater than the stall angle for the plain wing and contribute additional lift to the main airfoil. Leading-edge slats can be employed on wings to delay tip stalling, to increase maximum lift, to improve effectiveness of trailing-edge high-lift devices and therefore improve landing characteristics of some high-speed airplanes. The present investigation extends existing data on leading-edge slats to the NACA 6- series airfoils of low thickness ratios. The airfoils tested were the NACA 65A109 and NACA 641-212 sections. The optimum slat locations for maximum section lift coefficient were obtained at a Reynolds number of 2.0 X 106. With the slats at the optimum location the section aerodynamic characteristics were measured up to a Reynolds number of 9.0 X 106. | |
| language | English | |
| title | NACA-RM-L8K22 | num |
| title | Two-dimensional wind-tunnel investigation of two NACA 6-series airfoils with leading-edge slats | en |
| type | standard | |
| page | 46 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1949 | |
| contenttype | fulltext |
