Abstract
This study employs a numerical simulation method that combines the plasma body force model based on electrostatics with the Navier–Stokes equations to investigate the coupling mechanism of flow fields induced by multistage dielectric-barrier discharge (MDBD) actuation. Compared to conventional single-stage alternating-current DBD (AC-DBD) actuation, MDBD actuation provides higher actuation intensity and larger flow control region, which are advantageous for improving the flow control effect of DBD actuation. Numerical simulations are conducted based on the established MDBD flow control technology to study the flow control of the dynamic stall of an airfoil. The mechanism by which MDBD actuation-induced vortices delay dynamic stall and accelerate flow reattachment under unsteady conditions is analyzed. A control effect comparison with single-stage AC-DBD actuation validates the technical advantages of MDBD actuation in improving the average aerodynamic force, delaying lift and momentum stall, reducing the hysteresis effect, suppressing negative aerodynamic damping, and accelerating flow reattachment.
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