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NACA-TN-763
Wind-tunnel investigation of two airfoils with 25-percent-chord Gwinn and plain flaps
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:17:21Z | |
| date available | 2017-09-04T17:17:21Z | |
| date copyright | 01/01/1940 | |
| date issued | 1940 | |
| identifier other | ZHYIYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/140692 | |
| description abstract | Aerodynamic force tests of an NACA 23018 airfoil with a Gwinn flap having a chord 25 percent of the overall chord and of an NACA 23015 airfoil with a plain flap having a 25-percent chord were conducted to determine the relative merits of the Gwinn and the plain flaps. The tests indicated that, based on speed-range ratios, the plain flap was more effective than the Gwinn flap. At small flap deflections, the plain flap had lower drag coefficients at lift-coefficient values less than 0.70. For lift coefficients greater than 0.70, however, the Gwinn flap at all downward flap deflections had the lower drag coefficients. | |
| language | English | |
| title | NACA-TN-763 | num |
| title | Wind-tunnel investigation of two airfoils with 25-percent-chord Gwinn and plain flaps | en |
| type | standard | |
| page | 14 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1940 | |
| contenttype | fulltext |
