Airfoil Flow Control at High Angle of Attack by Surface Oscillation
This paper presents a new method of high lift. device of wing. Fundamental idea, of this method is to control flow pattern on the wing surface by its small oscillation at high angle of attack. The oscillation energy is added to the flow, and, as a result, transition from laminar boundary layer to turbulent, one is accelerated. The effect on the whole characteristics of the wing is expected as that the stall angle of attack is increased and. consequently, the maximum lift is also increased. This effect is verified by both wind tunnel test and numerical simulation.
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