S0550204 高レイノルズ数におけるDBDプラズマアクチュエータを用いた翼周り乱流剥離制御のLES([S055-02]プラズマアクチュエータ(2))

Abstract

We have conducted large-eddy simulations of the turbulent separation control by the DBD plasma actuator over NACA0015 airfoil. Reynolds number based on the chord length is 1,600,000 and the angle of attack is 20.1 degs. The location and operating conditions of the plasma actuator are changed as the numerical parameter. It is clarified that the effective mechanism for the turbulent-separation control by the burst mode is to induce the pairing of the large-scale vortex shed from the turbulent-separation shear-layer. The large-scale vortex results in the not only the momentum induction from freestream to the boundary layer but also the lift improvement through its convection. In addition to this control mechanism, various control effects can be achieved depending on the settings of the DBD plasma actuator.