| タイトル | Demonstration of Separation Control Using Glow-Discharge Plasma Actuators |
| 本文（外部サイト） | http://hdl.handle.net/2060/20030025722 |
| 著者（英） | Hultgren, Lennart S.; Ashpis, David E. |
| 著者所属（英） | NASA Glenn Research Center |
| 発行日 | 2003-01-01 |
| 言語 | eng |
| 内容記述 | Active flow control of boundary-layer separation using glow-discharge plasma actuators is studied experimentally. Separation is induced on a flat plate installed in a closed-circuit wind tunnel by a shaped insert on the opposite wall. The flow conditions represent flow over the suction surface of a modem low-pressure-turbine airfoil. The Reynolds number, based on wetted plate length and nominal exit velocity, is varied from 50,000 to 300,000, covering cruise to takeoff conditions. Low (0.2%) and high (2.5%) free-stream turbulence intensities are set using passive grids. A spanwise-oriented phased-plasma-array actuator, fabricated on a printed circuit board, is surface-flush-mounted upstream of the separation point and can provide forcing in a wide frequency range. Static surface pressure measurements and hot-wire anemometry of the base and controlled flows are performed and indicate that the glow-discharge plasma actuator is an effective device for separation control. |
| NASA分類 | Fluid Mechanics and Thermodynamics |
| 権利 | Copyright, Distribution as joint owner in the copyright |
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