Numerical Simulation of Flow Separation Control by Plasma Actuator in Burst Mode at Large Angles of Attack
Application of alternating current(AC)dielectric barrier discharge(DBD)plasma flow control is becoming the key research direction in plasma flow control technology due to its simple structure,fast response frequency,and the ability to achieve real-time quantitative control.The effect of flow separation control by plasma actuator in burst mode on NACA0015 airfoil at an angle of attack of 20° was investigated by using the method of detached eddy simulation(DES)separation vortex simulation and plasma-only body force model.The results show that the burst mode has a significant control effect on the airfoil under the condition of high Reynolds number and large angle of attack,it can achieve the purpose of increasing lift and reducing drag,and the flow separation control effect is more efficient than the steady mode.The mechanism of burst mode is different from the steady mode.The plasma actuator in burst mode suppresses the flow separation by promoting the velocity pulsation in the separation zone to produce unsteady interference in the flow field,which makes the separation shear layer destabilize earlier and enhances the mixing of the flow field vortex structure.
detached eddy simulation(DES)flow separation controlplasma actuator in burst mode
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