The relation between aerodynamic characteristics and the effectiveness of separation control with the DBD plasma actuator over the airfoil are discussed. The flow-fields around the NACA0015 airfoil are simulated with implicit large-eddy simulation using compact difference scheme. The normal mode generates moderately separated region over the airfoil and gains lift by negative pressure at the vortex center. The burst mode with nondimensional burst frequency of 1 enhances the vortex shedding from the separation shear layer and avoid the massive separation from the leading edge. However, the lift coefficient oscillate very much, in this case. The burst mode with nondimensional burst frequency of 6 improves the airfoil performance by suppressing the separation region. These facts indicate that the unsteady aerodynamic characteristics must be discussed when the effectiveness of separation control is evaluated.
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