抄録
This paper studied control of separated flow over an NACA0015 airfoil by a single dielectric barrier discharge (DBD) plasma actuator installed at the leading edge using large-eddy simulations with high-order accurate and high-resolution numerical scheme. A chord-based Reynolds number of 260,000 and an angle of attack of 18.8 degrees were considered. A phenomenological DBD plasma-actuator model was employed to provide the spatial body force distribution. The unsteady operation so-called a burst mode actuation was introduced and two burst frequencies of 1 and 6 with constant burst ratio of 0.1 were analyzed. Effects of the burst frequency on flow control performance were discussed in detail. Results showed DBD plasma actuator with burst frequency of 6 provided better control authority in comparison with the burst frequency of 1.
