Steuerung der Vorderkantenablosung an Einem Flugelprofil durch Lokale Anregung(Control of Leading-Edge Separation on an Airfoil by Localized Excitation)

摘要

The experimental investigation on the control of the separated flow over a lowReynolds number airfoil placed at high angles of attack was carried out. To reduce the separated flow and improve the airfoil's performance, some kind of periodic forcing can be used. A version of this control method consists in excitation of the flow through a narrow slot at the surface of the model near its leading edge. Such a technique was examined with emphasis on its operational principles. The study continues others concerning the use of a localized excitation for the separation control and makes clear some details about mechanisms responsible for the effect of the excitation on a separating flow.