タイトル | Experimental Results for a Flapped Natural-laminar-flow Airfoil with High Lift/drag Ratio |
本文(外部サイト) | http://hdl.handle.net/2060/19860016814 |
著者(英) | Harvey, W. D.; Pfenninger, W.; Viken, J. K.; Beasley, W. D.; Mcghee, R. J. |
著者所属(英) | NASA Langley Research Center |
発行日 | 1984-05-01 |
言語 | eng |
内容記述 | Experimental results have been obtained for a flapped natural-laminar-flow airfoil, NLF(1)-0414F, in the Langley Low-Turbulence Pressure Tunnel. The tests were conducted over a Mach number range from 0.05 to 0.40 and a chord Reynolds number range from about 3.0 x 10(6) to 22.0 x 10(6). The airfoil was designed for 0.70 chord laminar flow on both surfaces at a lift coefficient of 0.40, a Reynolds number of 10.0 x 10(6), and a Mach number of 0.40. A 0.125 chord simple flap was incorporated in the design to increase the low-drag, lift-coefficient range. Results were also obtained for a 0.20 chord split-flap deflected 60 deg. |
NASA分類 | AERODYNAMICS |
レポートNO | 86N26286 NAS 1.15:85788 NASA-TM-85788 |
権利 | No Copyright |
URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/65637 |