Experiments in Fluids

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

Airfoil boundary layer separation and control at low Reynolds numbers

Short Communications


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.


Fundamental Frequency Separation Bubble Boundary Layer Separation Separate Shear Layer Linear Stability Theory 



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


  1. Lang M, Rist U, Wagner S (2004) Investigations on controlled transition development in a laminar separation bubble by means of LDA and PIV. Exp Fluids 36:43–52Google Scholar
  2. Mueller TJ, DeLaurier JD (2003) Aerodynamics of small vehicles. Annu Rev Fluid Mech 35:89–111Google Scholar
  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

Personalised recommendations