Airfoil boundary layer separation and control at low Reynolds numbers
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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.
KeywordsFundamental 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.
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