バリア放電による翼面流れの剥離抑制効果 [in Japanese] Separation Control for Wing Surface Flow using Dielectric-barrier Discharge [in Japanese]
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The effect of momentum addition by a dielectric-barrier discharge was experimentally investigated. At first, flow induced by the discharge on a flat plate was investigated. Velocity profile was visualized by the smoke-wire technique and measured by a hot-wire anemometer. Maximum velocity was several meters per second at 1mm above the plate. Induced flow affect the velocity profile of boundary layer on the plate. Secondary, separation control for wing surface flow was investigated using a 9cm chord NACA0015 in a wind tunnel at 20m/s of air stream velocity (Re˜10<sup>5</sup>). Barrier discharge electrode was set on the leading edge of the wing. Separation angle was increased by 4 degrees and the maximum of the lift coefficient was improved by 17% with discharge power of 0.4W.
- IEEJ Transactions on Fundamentals and Materials
IEEJ Transactions on Fundamentals and Materials 128(4), 235-241, 2008-04-01
The Institute of Electrical Engineers of Japan