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http://dx.doi.org/10.6108/KSPE.2015.19.1.025

Aerodynamic Drag Reduction in Cylindrical Model Using DBD Plasma Actuator  

Lee, Changwook (Department of Aerospace Engineering, College of Engineering, Chosun University)
Sim, Ju-Hyeong (Department of Aerospace Engineering, College of Engineering, Chosun University)
Han, Sunghyun (Department of Aerospace Engineering, College of Engineering, Chosun University)
Yun, Su Hwan (High-speed Railroad Systems Department, Korea Railroad Research Institut)
Kim, Taegyu (Department of Aerospace Engineering, College of Engineering, Chosun University)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.19, no.1, 2015 , pp. 25-32 More about this Journal
Abstract
Dielectric barrier discharge (DBD) plasma actuator was designed to reduce aerodynamic drag in a cylindrical model and wind tunnel test was performed at various wind velocities. In addition, computational fluid dynamics (CFD) analysis and flow visualization were used to investigate the effect of the plasma on the flow stream in the cylinderical model. At low wind velocity, the plasma actuator had no effects because flow separation did not appear. The aerodynamic drag was reduced by 14% at 14 m/s and by 27% at 17 m/s, respectively. It was confirmed by CFD analysis and flow visualization that the DBD plasma actuator decreased in pressure difference around the cylindrical model, thus decreasing the magnitude of wake vortex.
Keywords
Plasma Flow Control; Aerodynamic Drag Reduction; Wind Tunnel Test; Plasma Actuator;
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Times Cited By KSCI : 1  (Citation Analysis)
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