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Airfoil boundary layer separation and control at low Reynolds numbers

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Abstract

The boundary layer separation on a NACA 0025 airfoil was studied experimentally via hot-wire anemometry and surface pressure measurements. The results provide added insight into periodic boundary layer control, suggesting that matching the excitation frequency with the most amplified disturbance in the separated shear layer is optimal for improving airfoil performance.

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Acknowledgements

The authors gratefully acknowledge the Natural Sciences and Engineering Research Council of Canada (NSERC) for the funding of this work.

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Authors and Affiliations

  1. Department of Mechanical and Industrial Engineering, University of Toronto, 5 King’s College Rd, Toronto, ON, M5S 3G8, Canada

    S. Yarusevych & P. E. Sullivan

  2. Department of Mechanical and Industrial Engineering, Ryerson University, 350 Victoria St., Toronto, ON, M5B 2K3, Canada

    J. G. Kawall

Authors
  1. S. Yarusevych
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  2. P. E. Sullivan
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  3. J. G. Kawall
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Correspondence to S. Yarusevych.

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Yarusevych, S., Sullivan, P.E. & Kawall, J.G. Airfoil boundary layer separation and control at low Reynolds numbers. Exp Fluids 38, 545–547 (2005). https://doi.org/10.1007/s00348-005-0943-2

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  • DOI: https://doi.org/10.1007/s00348-005-0943-2

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