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Numerical analysis of dynamic stall phenomena of an oscillating airfoil by the discrete-vortex approximation

  • Kiyoaki Ono
  • Kunio Kuwahara
  • Koichi Oshima
Contributed Papers
Part of the Lecture Notes in Physics book series (LNP, volume 141)

Abstract

The flow field around an oscillating airfoil under pitching and/or heaving motion was analized using the discrete-vortex approximation. The maximum angle of attack during oscillation was taken to be larger than the static stall one. The process of the formation of the leading edge separation vortex, its succeeding convection along the wing surface and its shedding into the wake was simulated. The dynamic lift stall curve was obtained when the reduced frequency defined with the half chord length was smaller than 0.25. When it was larger than 0.5, the dynamic lift stall did not occur.

Keywords

Unit Circle Wing Surface Moment Coefficient Discrete Vortex NACA Airfoil 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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References

  1. Carr, L.W., McAlister, K.W. & McCroskey, W.J. 1977 NASA TND-8382.Google Scholar
  2. Ham, N.D. 1968 AIAA Journal, vol.6, No.10.Google Scholar
  3. von Karman, T. & Sears, W.R. 1938 J.Aero. Sci., vol.5, No.10.Google Scholar
  4. Kuwahara, K. 1978 J. Phys. Soc. Japan, vol.45.Google Scholar
  5. Mehta, U.B. 1977 AGARD Paper 23.Google Scholar
  6. Theodorsen, T. 1935 NACA Report 496.Google Scholar

Copyright information

© Springer-Verlag 1981

Authors and Affiliations

  • Kiyoaki Ono
    • 1
  • Kunio Kuwahara
    • 2
  • Koichi Oshima
    • 3
  1. 1.Coll. Sci. & Tech.Nihon Univ.Tokyo
  2. 2.Dep. Appl. PhysicsUniv. TokyoTokyo
  3. 3.ISASUniv. TocsTokyo

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