G0501-3-5 Boundary Layer Bypass Transition on a Flat Plate affected Pressure Gradients : Effect of Strouhal number

Abstract

The purpose of this study is to investigate experimentally how factors affect the transitional behavior of the boundary layer on the blade. This paper deals with the effect of Strouhal number. The flow fields on the blade change from an accelerating flow to a decelerating flow. Especially, there are few research examples about the effect of the periodic wake passing through the deceleration flow field on the blade. Then precise experiments are demanded by many researchers. Wake-affected boundary layer bypass transition was evaluated using a Hot-Wire Anemometer to get the ensemble-averaged velocity and intermittency factor from the raw velocity data under the influence of adverse Pressure Gradients.