Flow control on a NACA 4418 using dielectric-barrier-discharge vortex generators

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[1] Jukes, Timothy N.
[2] Segawa, Takehiko
[3] Furutani, Hirohide
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Jukes, T.N. | 1600年 / AIAA International卷 / 51期
关键词：
Streamwise oriented Dielectric-Barrier-Discharge plasma actuators were used on a NACA 4418 airfoil for flow separation control at Rec = 35 k and 95 k. Rows of symmetric and asymmetric actuators were located on the fore section of the suction surface; which were designed to create counterrotating and corotating streamwise vortex arrays; respectively. These could completely reattach the flow in the downstream of the actuators for α c = 35 k; and for α c = 95 k. The drag coefficient was reduced by 63% at α = 14 deg and the lift coefficient increased by 67%; while the symmetric actuators performed slightly better than the asymmetric actuators overall. Streamwise vortices appeared to play a key role at low angles of attack; although the flow reattachment is believed to be primarily due to a strong suction into the plasma. Furthermore; these streamwise actuators outperformed a pair of spanwise actuators over the same chord-wise locations. Copyright © 2012 by the American Institute of Aeronautics and Astronautics; Inc. All rights reserved;
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Conference article (CA)
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