The sequence of events comprising dynamic stall of an airfoil is discussed, with emphasis on the role of the leading edge laminar separation bubble and shed vortex. A simple bubble model, hased on a combination of theoretical and experimental investigations, is used to discuss the events
prior to the shedding of the vortex, and provides the basis for a heuristic estimate of the delay in the occurrence of dynamic stall on a pitching airfoil. The evidence for the existence and dominant effect of the leading edge vortex on the dynamic stall required (but in most cases not presently
available) for the prediction of the effects of stall on helicopter rotor blades are discussed. It is the intention of this paper to focus attention on the laminar separation bubble and the shed lending edge vortex as the dominant features of the dynamic stall mechanism in the hope of stimulating
greater emphasis on these features in future dynamic stall research.
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Document Type: Research Article
U.S. Army Air Mobility R&D Laboratory, Moffett Field, California
Publication date: 1972-10-01
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