###### Abstract
[5] proposed using steady suction control to reduce the across-wind loading on a high-rise building and found that this control method disturbed the motion or development of large-scale leading edge vortices. [PERSON] et al. [6] used two small affiliated rotating cylinders to reduce the drag of a circular cylinder by suppressing the vortex shedding. [PERSON] et al. [7] found that a slot synthetic jet located at the rear surface of a square cylinder was used to achieve a drag reduction and shorten the wake vortex formation length. However, these active strategies require complex moving parts or mechanical configuration. The dielectric barrier discharge (DBD) plasma actuators can be divided into volume discharge actuators and surface discharge actuators. If the electrodes are located on both sides of a dielectric barrier layer, the plasma actuators are called surface DBD (SDBD) actuators; otherwise, they are volume DBD actuators. Since the volume DBD actuators are not suitable for flow control [8], the multi-SDBD plasma actuators are employed in the present study to explore plasma-based flow-control strategies. The main features of the actuators over other active control methods are their small size, light weight, quick response times, and easy installation because of the absence of moving parts. A single-SDBD plasma actuator is a very simple device consisting of asymmetric upper and lower electrodes separated by a dielectric plate. A power supply is applied on two electrodes to produce low-temperature plasma at the actuator surface. Under the action of the strong electric field, the plasma collides with surrounding neutral molecules and transfers its momentum to the ambient fluid, thereby a body force is created above the dielectric. The body force can induce a wall jet in quiescent air, and in an existing flow the body force is employed to get a beneficial modification of the mean velocity profile of the near-wall flow [9]. [PERSON] et al. [10] proposed that the drag reduction of a scaled train model can be obtained by using a SDBD plasma actuator to suppress the flow separation. They also found that the surface temperature of the dielectric and the induced flow velocity were increased as the applied voltage increased. The increased surface temperature may not affect the flow field around the train model. [PERSON] et al. [11] pointed out that two SDBD plasma actuators can reduce the vortex noise of a cylinder by 10 dB with the reduction of wake width and turbulent level. According to the experimental research of plasma flow control for a delta wing, [PERSON] et al. [12] believed that continuous plasma actuation with the airflow direction can delay the vortex breakdown to improve the wing lift. These studies show that the actuators have broad application prospects in flow control. At present, there are two types of mathematical models for plasma actuators: the first-principles model and the phenomenological model. The first-principles model appears to describe the charging process of the plasma and capture the basic physical quantities necessary to accurately estimate body force distributions [13]. However, this model involves complex chemical equations and difficult solution processes for Navier-Stokes equations, resulting in long computational time and massive storage consumption. These factors hinder the usability of this model. In contrast, since the phenomenological model is relatively easy to implement and has less computational costs, it is more suitable for application in research studies. The phenomenological model proposed by [PERSON] et al. [14] was successfully applied to the simulations of plasma-controlled flows around different obstacles. [PERSON] et al. [15] used this model to mitigate unsteady vortex shedding and flow separation around a circular cylinder, and the results showed that the mean drag was reduced by over 50% and the oscillatory lift was virtually eliminated. [PERSON] et al.