An experimental investigation of the three dimensional laminar boundary layer separation associated with an incident swept shock wave was conducted in the von Karman Institute (VKI) S-1 supersonic wind tunnel operating at Mach 2.15. Mean velocity profiles were measured both in the attached separated and reattachment flow regions using a laser doppler velocimeter. A comparison of the measurements with a full 3D Navier-Stokes solver, developed at the VKI, exhibited good agreement in all three regions, thus validating the code which was based on the Beam-Warming algorithm. The report also reviews the earlier parts of the grant dealing with the necessary developments in LDV to achieve high quality data, and the of the 2D shock boundary layer interaction. Keywords: Two dimensional flow; Three dimensional flow; Laminar boundary layer; Flow separation.

Single component LDV (Laser Doppler Velocimetry) measurements were obtained in the separated 2D thin laminar boundary layer over an elliptic cylinder. The ellipse had an axis ratio of 4:1 and the incoming Reynolds numbers based on the minor axis were 675 and 1350. Velocity measurements were obtained within 0.05 mm from the surface both in attached and reverse flow regions. Painting the model with matt black paint and covering the tunnel walls proved to be effective means of improving signal quality. Measurements were successful both in back and forward scatter modes. The velocity profiles measured with Bragg cells indicate that the flow is separated at the ellipse mid-chord and that the separation bubble extends far downstream in the wake. The velocity profiles in the attached flow region compare well with the results of a boundary layer computation.

Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines. SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.

This book presents experimental and numerical findings on reducing shock-induced separation by applying transition upstream the shock wave. The purpose is to find out how close to the shock wave the transition should be located in order to obtain favorable turbulent boundary layer interaction. The book shares findings obtained using advanced flow measurement methods and concerning e.g. the transition location, boundary layer characteristics, and the detection of shock wave configurations. It includes a number of experimental case studies and CFD simulations that offer valuable insights into the flow structure. It covers RANS/URANS methods for the experimental test section design, as well as more advanced techniques, such as LES, hybrid methods and DNS for studying the transition and shock wave interaction in detail. The experimental and numerical investigations presented here were conducted by sixteen different partners in the context of the TFAST Project. The general focus is on determining if and how it is possible to improve flow performance in comparison to laminar interaction. The book mainly addresses academics and professionals whose work involves the aerodynamics of internal and external flows, as well as experimentalists working with compressible flows. It will also be of benefit for CFD developers and users, and for students of aviation and propulsion systems alike.