Elementary atmosphere plasma flow control experiment is performed. Atmosphere plasma is generated on the surface of plasma actuator and the phenomenon of asymmetric plasma actuator inducing boundary layer to accelerate is verified. It is found that in the case of laying a symmetric actuator and an asymmetric actuator in bridge and vertically, the acceleration phenomenon of boundary layer on the surface of asymmetric actuator will disappear and a vortex motion of boundary layer on the surface of symmetric actuator will arise. The effectiveness of using plasma actuation to suppress airfoil stall separation is verified.