Download or read book Shock Wave Boundary Layer Interactions written by Holger Babinsky and published by Cambridge University Press. This book was released on 2011-09-12 with total page 481 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Experimental Studies of Shock Wave boundary Layer Interaction written by Michael S. Holden and published by . This book was released on 1974 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Transition Location Effect on Shock Wave Boundary Layer Interaction written by Piotr Doerffer and published by Springer Nature. This book was released on 2020-07-30 with total page 540 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Two dimensional Shock Wave boundary Layer Interactions in High Speed Flows written by Wilbur L. Hankey and published by . This book was released on 1975 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Investigation of Shock Wave turbulent Boundary Layer Interactions with and Without Boundary Layer Suction written by C. C. Sun and published by . This book was released on 1977 with total page 916 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tabulated data from a series of experimental studies of the interaction of a shock wave with a turbulent boundary layer in axisymmetric flow configurations is presented. The studies were conducted at the walls of circular wind tunnels and on the cylindrical centerbody of an annular flow channel. Detailed pitot pressure profiles and wall static pressure profiles upstream of, within and downstream of the interaction region are given. Results are presented for flows at nominal freestream Mach Numbers of 2, 3 and 4. For studies at the tunnel sidewalls, the shock waves were produced by conical shock generators mounted on the centerline of the wind tunnel at zero angle of attack. The annular ring generator was used to produce the shock wave at the centerbody of the annular flow channel. The effects of boundary layer bleed were examined in the investigation. Both bleed rate and bleed location were studied. Most of the bleed studies were conducted with bleed holes drilled normal to the wall surface but the effects of slot suction were also examined. A summary of the principal results and conclusions is given.

Download or read book Two dimensional Shock Wave boundary Layer Interactions in High Speed Flows Part 1 Theoretical Developments in Supersonic Separated Flows Part 2 Experimental Studies on Shock Wave boundary Layer Interaction written by Wilbur L. Hankey (Jr.) and published by . This book was released on 1975 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Studies of Hypersonic Shock Wave Boundary Layer Interactions written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-11-02 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two classes of shock-wave boundary-layer interactions were studied experimentally in a shock tunnel in which a low Reynolds number, turbulent flow at Mach 8 was developed on a cold, flat test surface. The two classes of interactions were: (1) a swept interaction generated by a wedge ('fin') mounted perpendicularly on the flat plate; and (2) a two-dimensional, unseparated interaction induced by a shock impinging near an expansion corner. The swept interaction, with wedge angles of 5-20 degrees, was separated and there was also indication that the strongest interactions prossessed secondary separation zones. The interaction spread out extensively from the inviscid shock location although no indication of quasi-conical symmetry was evident. The surface pressure from the upstream influence to the inviscid shock was relatively low compared to the inviscid downstream value but it rose rapidly past the inviscid shock location. However, the surface pressure did not reach the downstream inviscid value and reasons were proposed for this anomalous behavior compared to strongly separated, supersonic interactions. The second class of interactions involved weak shocks impinging near small expansion corners. As a prelude to studying this interaction, a hypersonic similarity parameter was identified for the pure, expansion corner flow. The expansion corner severely damped out surface pressure fluctuations. When a shock impinged upstream of the corner, no significant changes to the surface pressure were found as compared to the case when the shock impinged on a flat plate. But, when the shock impinged downstream of the corner, a close coupling existed between the two wave systems, unlike the supersonic case. This close coupling modified the upstream influence. Regardless of whether the shock impinged ahead or behind the corner, the downstream region was affected by the close coupling between the shock and the expansion. Not only was the mean pressure distribution modified but the un...

Download or read book Theoretical and Experimental Studies of Shock Wave laminar Boundary Layer Interaction in the Strong Interaction Regime written by Michael S. Holden and published by . This book was released on 1967 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Studies of Transitional Boundary Layer Shock Wave Interactions written by and published by . This book was released on 2006 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: Transitional shock wave/boundary layer interactions are studied with planar imaging techniques. The interaction is generated by a cylinder mounted on a flat plate in a Mach 5 flow. Planar laser scattering (PLS) and particle image velocimetry (PIV) are used to visualize the flow structure. Images are obtained in streamwise-spanwise planes (plan view). Earlier work focused on investigating similar interactions with tripped boundary layers, whereas the current work focuses on the case where transition occurs naturally. One goal of this preliminary study was to see if repeatable interactions could be generated. Imaging was conducted for three downstream locations of the cylinder. The PLS imaging revealed that the transitional interactions resulting from an untripped boundary layer are similar to those generated by tripping. In general it is observed that the separated flow region of transitional interactions exhibits larger variations in their scale and shape than fully turbulent interactions. When the cylinder is farthest upstream (5.3 diameters from leading edge) two types of separation shock are seen: an apparently laminar shock along the plate centerline and a turbulent one in the outboard region. As the cylinder is moved downstream (10.7 diameters), this dual structure is not as apparent, which is consistent with the upstream boundary layer becoming more turbulent. Finally, at 16 diameters downstream the interaction exhibits extreme variations in its shape, which we believe to be caused by sidewall interference. The PIV measurements largely confirm these qualitative observations.

Download or read book Theoretical and Experimental Studies of the Shock Wave boundary Layer Interaction on Compression Surfaces in Hypersonic Flow written by Michael S. Holden and published by . This book was released on 1970 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).

Download or read book Theoretical and Experimental Studies of the Shock Wave boundary Layer Interaction on Curved Compression Surfaces written by Michael S. Holden and published by . This book was released on 1969 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt: The paper describes a study of attached and separated laminar boundary layers over highly cooled, curved compression surfaces in a hypersonic airflow. In the theoretical study, the integral forms of the boundary layer equations for the conservation of mass, streamwise momentum, normal momentum, moment of streamwise momentum and energy were used to describe the development of attached and separated boundary layers on a curved 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. It was found that separation first occurred on the compression surface downstream of the flat plate, and incipient separation could not always be detected by observing the first occurrence of an inflexion point in the pressure distribution. (Author).

Download or read book Experimental Studies of Laminar Separated Flows Induced by Shock Wave boundary Layer and Shock shock Interaction in Hypersonic Flows for CFD Validation written by Michael S. Holden and published by . This book was released on 2000 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Investigation of the Shock Wave turbulent Boundary Layer Interaction written by David William Kuntz and published by . This book was released on 1985 with total page 544 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Investigation Into the Shock Wave boundary Layer Interaction on a 6 wedge written by Carl M. Putnam and published by . This book was released on 1991 with total page 198 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Methods of Shock Wave Research written by Ozer Igra and published by Springer. This book was released on 2015-10-31 with total page 480 pages. Available in PDF, EPUB and Kindle. Book excerpt: This comprehensive and carefully edited volume presents a variety of experimental methods used in Shock Waves research. In 14 self contained chapters this 9th volume of the “Shock Wave Science and Technology Reference Library” presents the experimental methods used in Shock Tubes, Shock Tunnels and Expansion Tubes facilities. Also described is their set-up and operation. The uses of an arc heated wind tunnel and a gun tunnel are also contained in this volume. Whenever possible, in addition to the technical description some typical scientific results obtained using such facilities are described. Additionally, this authoritative book includes techniques for measuring physical properties of blast waves and laser generated shock waves. Information about active shock wave laboratories at different locations around the world that are not described in the chapters herein is given in the Appendix, making this book useful for every researcher involved in shock/blast wave phenomena.

Download or read book An experimental investigation of shock wave turbulent boundary layer interactions with and without boundary layer suction written by Chen-Chih Sun and published by . This book was released on 1977 with total page 916 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Studies of Shock Wave Wall Jet Interaction in Hypersonic Flow written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-24 with total page 234 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental studies have been conducted to examine slot film cooling effectiveness and the interaction between the cooling film and an incident planar shock wave in turbulent hypersonic flow. The experimental studies were conducted in the 48-inch shock tunnel at Calspan at a freestream Mach number of close to 6.4 and at a Reynolds number of 35 x 10(exp 6) based on the length of the model at the injection point. The Mach 2.3 planar wall jet was generated from 40 transverse nozzles (with heights of both 0.080 inch and 0.120 inch), producing a film that extended the full width of the model. The nozzles were operated at pressures and velocities close to matching the freestream, as well as at conditions where the nozzle flows were over- and under-expanded. A two-dimensional shock generator was used to generate oblique shocks that deflected the flow through total turnings of 11, 16, and 21 degrees; the flows impinged downstream of the nozzle exits. Detailed measurements of heat transfer and pressure were made both ahead and downstream of the injection station, with the greatest concentration of measurements in the regions of shock-wave/boundary layer interaction. The major objectives of these experimental studies were to explore the effectiveness of film cooling in the presence of regions of shock-wave/boundary layer interaction and, more specifically, to determine how boundary layer separation and the large recompression heating rates were modified by film cooling. Detailed distributions of heat transfer and pressure were obtained in the incident shock/wall-jet interaction region for a series of shock strengths and impingement positions for each of the two nozzle heights. Measurements were also made to examine the effects of nozzle lip thickness on cooling effectiveness. The major conclusion from these studies was that the effect of the cooling film could be readily dispersed by relatively weak incident shocks, so the peak heating in the recompression region was not sig...