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Numerical and Experimental Investigation on Dynamic Stall Vortex

  • Junichi Miyakawa
  • Yuichi Shimbo
  • Shigeru Aso
Conference paper
Part of the International Union of Theoretical and Applied Mechanics book series (IUTAM)

Summary

The flow physics of dynamic stall vortex on a thin airfoil is probed by wind tunnel testing and computational analysis. The two-dimensional wind tunnel testing with unsteady pressure measurement reveals the creation and development of the leading edge and the trailing edge dynamic vortices. Also conducted in the test is the smoke wire technique together with the high speed video recording, which visualizes the detailed spatial and timewise mechanism of the dynamic vortices. The key feature of the leading edge vortex is that the airfoil pitching motion creates strong suction field near the leading edge to supply rotational energy to the leading edge vortex before it eventually convects downstream. The similar process is observed for the trailing edge vortex in downstroke motion. The numerical simulation with the discrete vortex method displays the vortex motion consistent with the experimental visualization, and the calculated streamline well correlates with the test result.

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References

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    McCroskey, W.J.: The Phenomenon of Dynamic Stall: NASA TM8I264, 1981Google Scholar
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    Walker, J., Helin, H. and Chou, D.: Unsteady Surface Pressure Measurements on a Pitching Airfoil: AIAA Paper 85–0532, 1985Google Scholar
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    Aso, S., Hayashi, M., Futatsudera, N. and Fujimoto, A.: Numerical Simulation of Separated Flow around a Wing Section by Discrete Vortex Method: Proc. of the Int. Symp. in Computational Fluid Dynamics, Nagoya, pp 810–816, 1989Google Scholar
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    Ghia, K.N.,Yang, J.,Osswald, G.A. and Ghia, U.: Study on the Dynamic Stall Mechanism Using Simulation of Two-Dimensional Navier-Stokes Equations: AIAA Paper 91–0546, 1991Google Scholar
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    Yanagizawa, M.: Calculations for Steady and Unsteady Aerodynamic Characteristics for Complex Configurations in Subsonic Flow: Boundary Integral Method in Fluid Engineering, pp209–226, 1990.Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 1993

Authors and Affiliations

  • Junichi Miyakawa
    • 1
  • Yuichi Shimbo
    • 1
  • Shigeru Aso
    • 2
  1. 1.Aerodynamics Research Section, Nagoya Aerospace SystemsMitsubishi Heavy Industries, Ltd.Japan
  2. 2.Department of Aeronautics and AstronauticsKyushu UniversityJapan

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