This investigation addresses the boundary layer study of a plunging airfoil. It specifically concerns the effect of reduced frequency on transition and separation/reattachment of the unsteady boundary layer. The wind tunnel measurements were conducted using multiple hot-film sensors, pressure transducers and a boundary-layer rake, at Reynolds numbers of 0.42 to 0.84 million, and over reduced frequencies from 0.05 to 0.11. It was observed the boundary layer transition occurs by a laminar separation bubble. The unsteady laminar separation is promoted (delayed) by the increase of the reduced frequency in upstroke (downstroke) portion of the equivalent angle of attack.
Effect of Reduced Frequency on the Boundary Layer of a Plunging Airfoil
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Rasi Marzabadi, F, Soltani, MR, & Masdari, M. "Effect of Reduced Frequency on the Boundary Layer of a Plunging Airfoil." Proceedings of the ASME 2010 10th Biennial Conference on Engineering Systems Design and Analysis. ASME 2010 10th Biennial Conference on Engineering Systems Design and Analysis, Volume 1. Istanbul, Turkey. July 12–14, 2010. pp. 185-190. ASME. https://doi.org/10.1115/ESDA2010-24574
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