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NACA-CB-L4G10
Wind tunnel investigation of NACA 66(215)-216, 66,1-212, and 65(sub 1)-212 airfoils with 0.20-airfoil-chord split flaps
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:28:35Z | |
| date available | 2017-09-04T15:28:35Z | |
| date copyright | 01/01/1944 | |
| date issued | 1944 | |
| identifier other | NUUYYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/29672 | |
| description abstract | INTRODUCTION Extensive tests of split flaps and other type of high-lift device used in conjunction with the older conventional airfoils have been conducted in wind tunnels and in flight. Because of the data available and because of the simplicity of this device, the split flap may conveniently be used as a basis for comparing the maximum-lift characteristics of various airfoil sections equipped with trailing-edge high-lift devices. The present investigation was carried out in the NACA two dimensional low-turbulence pressure tunnel to supply information on the maximum-lift and pitching-moment characteristics of three low-drag airfoil sections with split flaps. The NACA 66(215)-216, the NACA 66,1-212, AND the NACA 651-212 airfoils were equipped with split flaps having chords 20 percent of the airfoil chords (0.20c).Lift and pitching-moment data were obtained for each airfoil for a range of flap deflection from 400 to 700 at a Reynolds number of approximately 6X106. Because the tests were conducted at a mach number of approximately 0.15, the results are believed to be free from the effects of compressibility. | |
| language | English | |
| title | NACA-CB-L4G10 | num |
| title | Wind tunnel investigation of NACA 66(215)-216, 66,1-212, and 65(sub 1)-212 airfoils with 0.20-airfoil-chord split flaps | en |
| type | standard | |
| page | 16 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1944 | |
| contenttype | fulltext |
