采用多重介电阻挡放电(DBD)等离子体制动器控制高升力翼型下弯襟翼的流动分离
In current wing design, multiple flaps are incorporated into the trailing edge to allow mixing ofhigh and low pressure sides to reduce flow separation. These flaps reduce the efficiency byadding weight and complexity to the aircraft. A single hinged flap would reduce theseinefficiencies but is more susceptible to flow separation. Active flow control is a means bywhich the fluid flow over a body is deliberately altered and can be altered such that it becomesless likely to separate from the object. By energizing the flow, the degree of separation of theflow can be controlled, and this inherently controls lift. Dielectric barrier discharge (DBD)plasma actuators are a form of active flow control. These actuators are created byasymmetrically aligning two electrodes and adding a dielectric layer between the electrodes.When the electrodes are electrically connected, ionized air (plasma) travels from the exposedelectrode towards the covered electrode. Collisions occur between the plasma and neutral airover the body, and momentum is transferred to the neutral air, effectively energizing it. Thepurpose of this study is to examine the lift enhancement and flow control authority that multipleDBD plasma actuators have on a high-lift airfoil when compared to the flow exhibited by noncontrolledand single DBD plasma actuator controlled cases. Electrodes were mounted onto asimplified NASA Energy Efficient Transport airfoil near the flap. The airfoil was tested in aclosed, recirculating wind tunnel operating at a Reynolds number of 240,000, 20° flap deflectionangle and 0° degree angle of incidence. The actuators were independently powered in order todetermine the most effective input parameters. Using multiple actuators operated in-phase hasincreased the lift and has delayed flow separation on the trailing edge flap when compared tobaseline and single actuation cases.