This paper describes an experimental investigation of a transonic shock wave - turbulent boundary layer interaction in a curved test section, in which the flow has been computed by a 2-D Euler flow method. The test section has been designed such that the flow near the shock wave on the convex curved wall corresponds to that near the shock wave at the upper surface of a transonic airfoil. The aim of the present experiment was to produce carefully the conditions prevailing along the upper surface of an airfoil in transonic flow. Attention is paid to the effects of surface curvature and static pressure rise downstream of the shock wave on boundary layer parameters and separation phenomena.
|Tijdschrift||Delft Progress Report|
|Nummer van het tijdschrift||4|
|Status||Gepubliceerd - 1988|