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Plasma flow control, based on the plasma aerodynamic actuation, is a novel active flow control technique to improve aircraft aerodynamic characteristics and propulsion efficiency. This paper reports electrical and induced flow characteristics of plasma aerodynamic actuation generated by polyphase dielectric barrier discharge. Discharge of both symmetric and asymmetric plasma aerodynamic actuator is diffuse but filamentary. The induced flow characteristics of plasma aerodynamic actuation are experimentally investigated using Particle Image Velocimetry. Both symmetric and asymmetric plasma aerodynamic actuation generate starting vortex firstly, then the vortex evolves into a near-wall jet. The induced flow direction of symmetric polyphase plasma aerodynamic actuation can be changed by adjusting the phase of the adjacent electrodes. The induced flow direction of asymmetric polyphase plasma aerodynamic actuation can not be changed, but the induced flow velocity can be increased by adjusting the phase of the adjacent electrodes.