A Numerical Model for Modeling the Effect of Plasma Actuators in Flow Control.

This work presents the study of the single-dielectric barrier discharge aerodynamic plasma actuator. In this study a new computational model is proposed to simulate the flow control effects of glow discharge plasma. The strategy used in this project, is considering the plasma induced velocity, and investigating the effect of this velocity, on overall aerodynamic characteristics. The experimental patterns for plasma induced velocities, based on the applied voltage and frequencies, were used to model the plasma jet. A test case of NACA 4412 was used to show the effect of using the plasma actuator