Study on drag coefficient via dielectric barrier discharge (DBD) plasma actuators

Abstract

Nowadays, due to the wide application and importance of active control methods such as Dielectric Barrier Discharge (DBD) plasma actuators, they are used in industries such as aerospace, propellers, and wind turbines to reduce the flow separation region and vortices around these objects (important applications). Accordingly, theories that can improve the efficiency in the aviation industry have drawn much attention. The larger the flow separation region around the airfoil, the more the vortices and return flows, and the larger the drag force. This leads to undesirable dissipation, especially in fuel, and instability of the aircraft (importance of the research work). The drag coefficient has a significant effect on the performance of the airplane, especially at high velocities. Hence, a method that can control the air flow on the airfoil and decrease the drag coefficient and the associated dissipation will be helpful. In this research, the airflow over a NACA0012 airfoil has been designed and analyzed in ANSYS Fluent software. In this method, two-dimensional airfoil aerodynamics is considered, and the high-Re airflow around the airfoil is analyzed. Moreover, the UDF code of the plasma is defined as a body force at an optimal and sensitive location of the airfoil (flow separation region). Subsequently, the drag coefficient is evaluated at a constant Re and different angles of attack. As a result, the drag coefficient at different angles of attack is smaller for when plasma is defined on the airfoil (plasmaon) compared to when plasma is inactive (plasma-off). Furthermore, it is shown that the pressure distribution around the airfoil is improved using plasma actuators.