Novel Computational Electrodynamic Model for The Simulation of Plasma-based Flow Control Actuator Effect on Aerodynamic Performance Improvement

On the basis of the properties of low-frequency plasmons, a novel phenomenological model for simulating dielectric barrier discharge (DBD) actuators for separation control of flow over a wind turbine airfoil is presented. Within the Navier Stokes equations, the model simulates the plasmonic region as a dispersive medium, including the effects of the plasma actuator on the flow. The model solves Poisson s equation for the electric field and simplifies the Lorentz model for the polarization field in order to compute the corresponding body force vector field. The model is then validated using experimental data derived from momentum exchange with a neutrally charged fluid under a variety of electrode operation voltages. After determining the applicability of the plasma-based actuator mounted on an SD7003 airfoil, the plasma-induced flow characteristics are investigated. The results revealed that plasma actuation has delayed separation and enhanced the airfoil s aerodynamic performance, resulting in an increase of 0.85 percent and 8.39 percent in the lift coefficient, a decrease of 5.12 percent and 19 percent in the drag coefficient, and an increase of 15.8 percent and 72.8 percent in the lift to drag ratio for the 10-degree and 15-degree angle of attack (AOA) cases, respectively. The actuator has significantly reduced or eliminated the separated region, demonstrating the computational model s applicability to the simulation of the studied plasma-hydrodynamic flow.