سال انتشار: ۱۳۸۸

محل انتشار: هشتمین همایش انجمن هوافضای ایران

تعداد صفحات: ۶

نویسنده(ها):

A Abdoli – Dept. of Physics, Sharif University of Technology, Tehran, Iran – Research student (corresponding author)
A Anvari – Dept. of Physics, Sharif University of Technology, Tehran, Iran – Associate professor

چکیده:

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.