Active Control of the Compressible Boundary Layer on an Infinite Supersonic Swept Wing with a Supersonic Leading Edge by Suction and Cooling

A study of the laminar/turbulent transition have been conducted at the Institute of Design Aerodynamics (DLR Braunschweig) in order to investigate new supersonic configurations. By means of boundary- layer computations and transition predictions based on the linear stability theory, the potential of different boundary-layer control methods has been shown for delaying the transition over a infinite supersonic swept wing with a supersonic leading edge. The methods presented in this paper to delay the transition are suction and wall cooling. As far as laminarization is concerned, both seem to have great potential