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| Author | : Michael S. Holden |
| Publisher | : |
| Total Pages | : 0 |
| Release | : 1967 |
| Genre | : Laminar boundary layer |
| ISBN | : |
| Author | : Holger Babinsky |
| Publisher | : Cambridge University Press |
| Total Pages | : 481 |
| Release | : 2011-09-12 |
| Genre | : Technology & Engineering |
| ISBN | : 1139498649 |
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.
| Author | : Michael S. Holden |
| Publisher | : |
| Total Pages | : 178 |
| Release | : 1967 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
The report describes a theoretical and experimental investigation of the properties of attached and separated regions of shock wave-laminar boundary layer interactions in the strong interaction regime. A study was made of the flow over a flat plate-wedge compression surface in the high Mach number, low Reynolds number regime where the interaction between the viscous and inviscid regions over the basic flat plate is 'strong' and of fundamental importance to the problem. The theoretical analysis described in the first part of the paper treats the development of the viscous layer and its interaction with the external inviscid stream, using an integral representation for the boundary layer equations. The analysis describes the strong interaction over the flat plate, the transition from a supercritical to a subcritical boundary layer upstream of the separation point, and the subsequent development of the viscous layer through to the end of the interaction. The theory was compared with experimental measurements in both strong and weak interaction regions of separated flow. The complementary experimental study described in the second part of the paper was designed to investigate the shock wave-boundary layer interaction on flat plate-wedge compression surfaces in the strong interaction regime. (Author).
| Author | : Michael S. Holden |
| Publisher | : |
| Total Pages | : 96 |
| Release | : 1975 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
This report describes a theoretical and experimental investigation of the properties of attached and separated regions of shock wave-laminar boundary layer interacting in the strong interaction regime. The flow is studied over a flat plate-wedge compression surface in the high Mach number, low Reynolds number regime where the interaction between the viscous and inviscid regions over the basic flat plate is strong and of fundamental importance to the problem. The theoretical analysis treats the development of the viscous layer and its interaction with the external inviscid stream, using an integral representation for the boundary layer equations. A complementary experimental study investigated the flow over a flat plate-wedge compression surface for a range of free-stream Reynolds number and Mach number conditions in the strong interaction regime.
| Author | : |
| Publisher | : |
| Total Pages | : 1264 |
| Release | : 1967 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : Earl C. Watson |
| Publisher | : |
| Total Pages | : 140 |
| Release | : 1969 |
| Genre | : Laminar boundary layer |
| ISBN | : |
Laminar and turbulent boundary layer interactions with externally generated shock waves.
| Author | : |
| Publisher | : |
| Total Pages | : 372 |
| Release | : 1994 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : Piotr Doerffer |
| Publisher | : Springer Nature |
| Total Pages | : 540 |
| Release | : 2020-07-30 |
| Genre | : Technology & Engineering |
| ISBN | : 3030474615 |
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.
| Author | : Michael S. Holden |
| Publisher | : |
| Total Pages | : 76 |
| Release | : 1970 |
| Genre | : |
| ISBN | : |
A detailed description is given of the theoretical and experimental studies of shock wave-laminar boundary layer interaction on curved compression surfaces in hypersonic flow. Integral forms of the boundary layer equations were used for the conservation of mass, streamwise momentum, normal momentum, moment of streamwise momentum and energy to describe the development of attached and separated boundary layers on a curve surface. In the experimental study, skin friction, heat transfer and pressure measurements were made on a series of flat plate-cylindrical arc-wedge compression surfaces. Pitot and cone pressure measurements were made above the surface in the separation and reattachment regions of separated flows to estimate the static pressure difference across the boundary layer. The radius of curvature of the cylindrical arc, the inclination of the wedge, and the unit Reynolds number of the free-stream were varied to examine their effect on the properties of both attached and separated interaction regions over the models. (Author).
| Author | : Wilbur L. Hankey |
| Publisher | : |
| Total Pages | : 20 |
| Release | : 1975 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
This report reviews the progress over the last decade on separated flows conducted at these laboratories. Experimental investigations conducted in the hypersonic wind tunnels is discussed. Advancements are summarized in the theoretical area which cover the development of interacting boundary layers to the numerical computation of the complete Navier-Stokes equations.
