22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-2.9.2

PHENOMENA OF DYNAMIC STALL ON SWEPT WINGS

J. Henkner
TU München & Dornier Luftfahrt GmbH, Germany

Keywords: boundary layer, three-dimensional, unsteady, separation

Surface pressure distributions on pitching swept wings show differences to equivalent twodimensional cases. With the aid of a newly developed hot wire probe flow fields of a threedimensional, unsteady boundary layer separation can be presented for the first time. The temporal evolution of the dynamic stall on a swept wing in sinusoidal motion is shown for a selected example. Comparative numerical results are principally in good agreement with the experiment. A refined generalized model for the onset of dynamic stall and the evolution of the vortex can be given from detailed analysis of the experimental and computational results. It becomes evident that the beginning of the stall is a process driven by boundary layer effects while the outer flow follows a quasi-steady progression until the onset of the dynamic stall vortex.

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