In current wing design, multiple flaps are incorporated into the trai领 edge to allow mixing of
high and low pressure sides to reduce flow separation. These flaps reduce the efficiency by
adding weight and complexity to the aircraft. A single hinged flap would reduce these
inefficiencies but is more susceptible to flow separation. Active flow control is a means by
which the fluid flow over a body is deliberately altered and can be altered such that it becomes
less likely to separate from the object. By energizing the flow, the degree of separation of the
flow 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 by
asymmetrically aligning two electrodes and adding a dielectric layer between the electrodes.
When the electrodes are electrically connected, ionized air (plasma) travels from the exposed
electrode towards the covered electrode. Collisions occur between the plasma and neutral air
over the body, and momentum is transferred to the neutral air, effectively energizing it. The
purpose of this study is to examine the lift enhancement and flow control authority that multiple
DBD plasma actuators have on a high-lift airfoil when compared to the flow exhibited by noncontrolled
and single DBD plasma actuator controlled cases. Electrodes were mounted onto a
simplified NASA Energy Efficient Transport airfoil near the flap. The airfoil was tested in a
closed, recirculating wind tunnel operating at a Reynolds number of 240,000, 20° flap deflection
angle and 0° degree angle of incidence. The actuators were independently powered in order to
determine the most effective input parameters. Using multiple actuators operated in-phase has
increased the lift and has delayed flow separation on the trai领 edge flap when compared to
baseline and single actuation cases. 德国LaVision PIV/PLIF粒子成像测速场仪
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