Airfoil Flow Control at High Angle of Attack by Surface Oscillation

  • M. Kobayakawa
  • Y. Kondo
  • H. Suzuki
Conference paper
Part of the International Union of Theoretical and Applied Mechanics book series (IUTAM)


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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Copyright information

© Springer-Verlag Berlin Heidelberg 1993

Authors and Affiliations

  • M. Kobayakawa
    • 1
  • Y. Kondo
    • 1
  • H. Suzuki
    • 1
  1. 1.Department, of Aeronautical EngineeringKyoto UniversityKyoto 606Japan

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