Experiments in Fluids

, Volume 38, Issue 4, pp 545–547 | Cite as

Airfoil boundary layer separation and control at low Reynolds numbers

Short Communications

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.

References

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  3. Yarusevych S, Kawall JG, Sullivan PE (2003) Effect of acoustic excitation on airfoil performance at low Reynolds numbers. AIAA J 41:1599–1601Google Scholar
  4. Zaman KBMQ (1992) Effect of acoustic excitation on stalled flows over an airfoil. AIAA J 30:1492–1499Google Scholar

Copyright information

© Springer-Verlag 2005

Authors and Affiliations

  1. 1.Department of Mechanical and Industrial EngineeringUniversity of TorontoTorontoCanada
  2. 2.Department of Mechanical and Industrial EngineeringRyerson UniversityTorontoCanada

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