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Fourth International Symposium on Turbulence and Shear Flow Phenomena
June, 27-29, 2005, Marriot Hotel, Williamsburg, Virginia, USA

DOI: 10.1615/TSFP4

Control of a decelerating boundary layer. Comparison of different actuators using PIV

pages 659-664
DOI: 10.1615/TSFP4.1110
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摘要

The control of boundary layer separation on the suction side of an airfoil at high angle of attack has been renewed by the possibilities of active control. Nevertheless, such an active control needs a deep understanding of the flow to manipulate and of the actuating flow, both being 3D and unsteady. For that purpose, a model experiment has been designed in the frame of a coordinated European project called AEROMEMS, with a simple (2D) geometry and with a dilatation of the scales in order to be able to characterize the actuation flow. This model is a bump in a boundary layer wind tunnel, which mimics the adverse pressure gradient on the suction side of an airfoil at the verge of separation. The present contribution describes tests performed in the frame of the AEROMEMS II project to compare standard passive devices with active jets systems. The optimization was done with hot film shear stress probes, the characterization with PIV. The results show quantitatively the improvement brought by the devices in terms of skin friction. They also show the mechanism which is at the origin of this improvement.

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