Experimental Study of Flow Control Over an Ahmed Body Using Plasma Actuator

EXPERIMENTAL INVESTIGATION OF DRAG REDUCTION ON AHMED MODEL USING A COMBINATION OF ACTIVE FLOW CONTROL METHODS

Aerodynamic drag is an important factor in vehicles fuel consumption. Pressure drag which is the main component of total drag is a result of boundary layer separation from vehicle surface. Flow control methods are applied to avoid or at least delay separation. Depending upon whether these methods consume energy to control the flow or not, they are called active or passive control methods. In th...

Flow Control over Conical Forebody with Port Pulsed Plasma Actuator

A study using plasma port single-pulsed discharge is performed on the flow control of asymmetrical vortices over slender conical forebody. The different circumferential steady and unsteady pressure distributions are measured in the wind tunnel test. At the same time, the local side force, the increment of local side force and the overall side force and moment are calculated with the circumferen...

experimental investigation of active flow control for changing stall angle of a naca0012 airfoil, using plasma-actuator

active flow control has great importance in design of flying objects in general and control flaps in particular. using dielectric barrier discharge as plasma actuators over control flaps can cause a change in position of separation point or can eliminate it. this new flow control device produces a body force that causes generating a micro wall jet. the present study aims to investigate experime...

Plasma Actuators for Bluff Body Flow Control

The aerodynamic plasma actuators have shown to be efficient flow control devices in various applications. In this study the results of flow control experiments utilizing single dielectric barrier discharge plasma actuators to control flow separation and unsteady vortex shedding from a circular cylinder in cross-flow are reported. This work is motivated by the need to reduce landing gear noise f...

Flow Control of Leading Edge Separation on Airfoil Using Dbd Plasma Actuator