Experimental Study On Discharge Characteristics And Aerodynamic Characteristics Of Plasma Actuator

Flow control has always been one of the most important problems in the design of aircraft.However,there is no effective way to control the flow in surface of aircraft and inside the engine.Plasma aerodynamic actuator has the advantages of simple structure,fast response and significant control effect,so it is very potential in low speed and ultra supersonic flow control.In this paper,the size of the electrode and the effect of dielectric material on CDBD are studied.Based on the optimized parameters of CDBD,a new low speed plasma actuator-TCBDB is proposed,and its discharge characteristics and induced airflow performance are experimentally studied.In addition,it is also compared with CDBD and SDBD actuator.For high-speed active flow control,a plasma synthetic jet device with a jet velocity of 120 m/s has been developed.The jet is accompanied by shock waves and reflection waves propagating at sound speed.Based on the electric parameter measurement system and the high speed schlieren system,the discharge characteristics and the flow field structure and development process of the plasma synthetic jet actuator are studied.The results show that the voltage peak,frequency and injection energy have great influence on the flow field of plasma synthetic jet,but the influence of voltage rising edge on jet flow field is not obvious,which provides a scientific basis for the optimization of plasma synthetic jet structure and the design parameters of high voltage impulse power supply.