Suppression of a boundary layer separation over an airfoil surface using a pulsed DBD plasma actuator at Re=30,000: Relationship between modulation frequency and behavior of vortexes flow
In low Reynolds numbers region's flow, a laminar separation region and separation bubble are observed on an airfoil surface, these separation flow contribute to deterioration aerodynamics of the airfoil. We intended to improve the aerodynamics of a NACA0012 airfoil using a pulsed DBD plasma actuator as a flow control device for suppressing the separated flow. We visualized the flow field around the NACA0012 airfoil and measured aerodynamic forces of the airfoil to examine an effect of induced flow by the plasma actuator at 30,000 of Reynolds number. The actuator was only driven in a pulsed modulation wave mode which both of the duty ratio DR and non-dimensional modulation frequency F(+). As the results, we confirmed that a maximum lift coefficient and a stall angle were changed by flow field existing vortices on the airfoil surface which depend on F(+) changing.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
Re＝30,000におけるDBDプラズマアクチュエータを用いた翼面上の境界層剥離の抑制: 変調周波数と渦の挙動の関係
AA1530023029.pdf
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