Abstract
Active flow control is introduced to the separated flow field over a swept wing through a streamwise row of vortex generating jets in order to encourage flow reattachment and augment lift performance. The wing with 30° leading-edge sweep angle and NACA 64(3)-618 cross-section exhibits a complex suction surface flow field, with a separation pattern strongly dependent on angle of attack. Separation is localized to the trailing edge for moderate angles while dynamics of a leading-edge vortex govern separation for higher angles. Surface oil flow visualization and particle image velocimetry are performed over a range of angles of attack to develop a more detailed understanding of the stalled flow development and the role of active flow control in altering the flow character. Reattachment is achieved outboard of the flow control actuators regardless of the nature of separation in the uncontrolled state. When the flow is separated at the leading edge, the flow control affects flow structures over inboard sections as well as outboard. The freestream Reynolds and Mach numbers are 10^5 and 0.05, respectively.
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