Fundamental Study of Shock Wave/Turbulent Boundary Layer Interactions withPassive Control in Transonic Flows

摘要

The techniques for controlling shock wave/turbulent boundary layer interactionare reviewed. A passive control device makes it possible to improve the performance of airfoils at transonic velocities. An interaction subjected to passive control was performed in a transonic channel. The flow is described by means of Schlieren visualization, measurements of pressure on the walls of the duct and two dimensional laser velocimetry. A momentum balance carried out in the control region made it possible to infer configurations for which the friction drag is reduced by comparison with the reference case without control. The theoretical study is based on a boundary layer type approach using the first order Prandtl equations. Experimental results obtained for the reference case and a case with control are compared.