| タイトル | The NASA Langley Laminar-Flow-Control Experiment on a Swept Supercritical Airfoil: Basic Results for Slotted Configuration |
| 本文（外部サイト） | http://hdl.handle.net/2060/19890012391 |
| 著者（英） | Harris, Charles D.; Clukey, Patricia G.; Brooks, Cuyler W., Jr.; Stack, John P. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1989-06-01 |
| 言語 | eng |
| 内容記述 | The effects of Mach number and Reynolds number on the experimental surface pressure distributions and transition patterns for a large chord, swept supercritical airfoil incorporating an active Laminar Flow Control suction system with spanwise slots are presented. The experiment was conducted in the Langley 8 foot Transonic Pressure Tunnel. Also included is a discussion of the influence of model/tunnel liner interactions on the airfoil pressure distribution. Mach number was varied from 0.40 to 0.82 at two chord Reynolds numbers, 10 and 20 x 1,000,000, and Reynolds number was varied from 10 to 20 x 1,000,000 at the design Mach number. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 89N21762
L-16474
NAS 1.15:4100
NASA-TM-4100 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/82573 |
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