Abstract
Compressor and turbine blade boundary layers in axial-flow turbomachines are subject to periodically disturbed flow. This study modelled these conditions in a wind tunnel with circular cylinders traversing in front of a flat plate. Turbulent boundary layer velocity profiles on the flat plate were measured with a hot-wire anemometer. The turbulence intensity in the boundary layer was found to be significantly increased by the unsteady freestream flow, resulting in increased characteristic boundary layer thicknesses and skin friction coefficient. The vortex structure within the unsteady cylinder wakes was found to explain the behaviour of the velocity and phase angle profiles in the boundary layer.
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