Plasma Actuator Effects on Flow over Airfoil with Different Angle of Attacks

In this paper, effects of plasma actuator have been studied in flow control over airfoil NACA0021. For simulating plasma actuator effects, the electrostatic model has been applied. It is based on the assumption of different time scales that play different roles in the physics of the plasma actuator and allows decoupling the problem into two separate parts associated with: the plasma body force formation and the fluid flow response. By using this model, it is possible to simulate plasma actuator effects by inducing a body force field into Navier-Stokes equations.Airflow velocity was 5 m/s. The plasma actuator has been located in the leading edge of the airfoil. The efficiency plasma actuator in different angle of attacks has been studied.

کلیدواژه ها:

Plasma actuator ، Flow control ، Separation ، Electrostatic model