Nihon University
College of Science and Technology, Nihon University
College of Science and Technology, Nihon University
College of Science and Technology, Nihon University
43rd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2011 (July 7-8, 2011. Waseda University, International Conference Center), Tokyo Japan
抄録（英）
Aerodymamic performance of NACA0012 airfoil is enhanced with suppression of boundary layer separation due to operation of DBD plasma actuator at low Reynolds numbers. We carried out flow field measurements using hot-wire anemometer around the airfoil which applied to the actuator to investigate relationship between aerodynamics and flow field around the airfoil at Reymolds number of 10,000. Results of velocity profiles of the boundary layer show suppression of laminar separation on the airfoil at lower angle of attack. At higher angle of attack, separated boundary layer on the airfoil is reattached on the surface by large velocity. fluctuations accompanied with shedding vortex by the actuator operation. These changes of the flow field due to the actuator contribute to enhance the lift coefncient of the airfoil.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
低レイノルズ数におけるDBDプラズマアクチュエータが作用するNACA0012翼型まわりの流れ場の特性
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