The flowfield structure about annular dielectric barrier discharge plasma actuators is studied under quiescent flow conditions using particle image velocimetry. These actuators are currently under investigation for use as spanwise-periodic discrete roughness elements for laminar flow control on swept wings in both the wind-tunnel and flight. Aperture diameters considered vary from 3mm to 7 mm. Additionally, an arrayed actuator of five 3 mm apertures is considered. A complex flowfield is found to be generated, which consists of two counter-rotating vortices accompanied by a wall-normal jet region. The flowfield structure is shown to be sensitive to aperture size and applied voltage. For the arrayed actuator, the vortices contract dramatically due to the interaction of adjacent vortices from neighboring apertures. This work is the first step towards understanding the physical mechanism(s) of plasma actuators as discrete roughness elements for laminar flow control on swept wings.