No abstract

No abstract

No abstract

The dielectric barrier discharge (DBD) plasma actuator has in the last decade emerged as an active flow control device. This paper investigates the experimental measurements concerning the instantaneous ionic wind velocity induced by DBD plasma actuator in quiescent air at atmospheric pressure. A parametric study has also been undertaken to find a realistic means of increasing the velocity of the ionic wind. The electrical and mechanical characteristics of the plasma actuator have been studied under different conditions. The aim of this article is to find ways of optimizing the geometrical and electrical parameters to obtain more effective ionic wind for flow control. The results show that increments in the excitation frequency, leads to maximum velocity at the nearer position of the surface. Further analysis show that the frequency of the vortices produced by the related actuators is exactly the same as the excitation frequency of the applied voltage. It was also found that an increase in the duty cycle correspondingly increases the power of the produced vortex shedding.

This paper aims at experimental investigation of the active flow control with plasma actuator over an airfoil. The method involved application of single dielectric barrier discharge in order to change the frequency of vortex shedding and the turbulence characteristics from a NACA4412 airfoil. The objective was to reduce control flaps noise in transporting aircraft via an effective body force generated by the actuators. Results indicated that the use of plasma actuator led to a significant decrease in the frequency of vortex shedding around the flap whereas a significant increase in turbulence levels was achieved at a distance away from the actuator.

No abstract

No abstract

No abstract