Download or read book Hypersonic Shock Wave Boundary Layer Interactions Over Compression Corners written by George Simeonides and published by . This book was released on 1992 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Two dimensional Compression Corner and Planar Shock Wave Interactions with a Supersonic Turbulent Boundary Layer written by C. Herbert Law and published by . This book was released on 1975 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Flow Separation in Shock Wave Boundary Layer Interactions at Hypersonic Speeds written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-10-28 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: An assessment is presented for the experimental data on separated flow in shock wave turbulent boundary layer interactions at hypersonic and supersonic speeds. The data base consists mainly of two dimensional and axisymmetric interactions in compression corners or cylinder-flares, and externally generated oblique shock interactions with boundary layers over flat plates or cylindrical surfaces. The conditions leading to flow separation and the subsequent changes in the flow empirical correlations for incipient separation are reviewed. The effects of the Mach number, Reynolds number, surface cooling and the methods of detecting separation are discussed. The pertinent experimental data for the separated flow characteristics in separated turbulent boundary layer shock interaction are also presented and discussed. Hamed, A. Unspecified Center...
Download or read book Hypersonic Shock Wave turbulent Boundary Layer Interactions in the Vicinity of an Expansion Corner written by Michael E. White and published by . This book was released on 1995 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Two Dimensional Compression Corner and Planar Shock Wave Interactions with a Supersonic Turbulent Boundary Layer written by C. Herbert Law and published by . This book was released on 1975 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental data have been obtained to describe the interactions between a turbulent boundary layer and (1) a two-dimensional compression corner and (2) an externally generated planar shock wave. Investigations were conducted at Mach number 3 over a range of Reynolds numbers from 10 to 100 million under adiabatic wall conditions. The effects of compression corner angle, planar shock wave strength, and Reynolds number on the length of separation and upstream influence were obtained. The incipient separation conditions and three-dimensional effects were also investigated. The separation and upstream influence lengths were found to increase with increasing Reynolds number for fixed overall pressure rise. The overall pressure rise for incipient separation is approximately the same for the compression corner interaction and the planar shock wave interaction, and increases with increasing Reynolds number. Turbulent boundary layer separation was found to be of the free interaction type, whereby the separation angle and the pressure distribution through separation were found to be independent of Reynolds number, overall pressure rise, and type of disturbance. For the case of the externally generated shock wave, the span of the shock generator had to be reduced in order to eliminate an initially significant influence of the sidewall shock wave-boundary layer interaction on the test region. (Author).
Download or read book Expansion Corner Effects on Hypersonic Shock Wave turbulent Boundary Layer Interactions written by Michael E. White and published by . This book was released on 1996 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Flow Separation in Shock Wave Boundary Layer Interactions at Hypersonic Speeds written by A. Hamed and published by . This book was released on 1990 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Documentation of Two and Three dimensional Hypersonic Shock Wave turbulent Boundary Layer Interaction Flows written by Marvin I. Kussoy and published by . This book was released on 1989 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Two Dimensional Compression Corner and Planar Shock Wave Interactions with a Supersonic Turbulent Boundary Layer written by and published by . This book was released on 1975 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental data have been obtained to describe the interactions between a turbulent boundary layer and (1) a two-dimensional compression corner and (2) an externally generated planar shock wave. Investigations were conducted at Mach number 3 over a range of Reynolds numbers from 10 to 100 million under adiabatic wall conditions. The effects of compression corner angle, planar shock wave strength, and Reynolds number on the length of separation and upstream influence were obtained. The incipient separation conditions and three-dimensional effects were also investigated. The separation and upstream influence lengths were found to increase with increasing Reynolds number for fixed overall pressure rise. The overall pressure rise for incipient separation is approximately the same for the compression corner interaction and the planar shock wave interaction, and increases with increasing Reynolds number. Turbulent boundary layer separation was found to be of the free interaction type, whereby the separation angle and the pressure distribution through separation were found to be independent of Reynolds number, overall pressure rise, and type of disturbance. For the case of the externally generated shock wave, the span of the shock generator had to be reduced in order to eliminate an initially significant influence of the sidewall shock wave-boundary layer interaction on the test region. (Author).
Download or read book Hypersonic and High Temperature Gas Dynamics written by John David Anderson and published by AIAA. This book was released on 1989 with total page 710 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book is a self-contained text for those students and readers interested in learning hypersonic flow and high-temperature gas dynamics. It assumes no prior familiarity with either subject on the part of the reader. If you have never studied hypersonic and/or high-temperature gas dynamics before, and if you have never worked extensively in the area, then this book is for you. On the other hand, if you have worked and/or are working in these areas, and you want a cohesive presentation of the fundamentals, a development of important theory and techniques, a discussion of the salient results with emphasis on the physical aspects, and a presentation of modern thinking in these areas, then this book is also for you. In other words, this book is designed for two roles: 1) as an effective classroom text that can be used with ease by the instructor, and understood with ease by the student; and 2) as a viable, professional working tool for engineers, scientists, and managers who have any contact in their jobs with hypersonic and/or high-temperature flow.
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 PERFECT GAS NAVIER STOKES SOLUTIONS OF HYPERSONIC BOUNDARY LAYER AND COMPRESSION CORNER FLOWS written by and published by . This book was released on 2005 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: W) on strong shock wave/boundary layer interactions with extended separated regions are investigated. The obtained results are compared with the available experimental data, computational results, and theory.
Download or read book Numerical Simulation of Supersonic Compression Corners and Hypersonic Inlet Flows Using the Rplus2d Code written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-12-29 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: A two-dimensional computational code, PRLUS2D, which was developed for the reactive propulsive flows of ramjets and scramjets, was validated for two-dimensional shock-wave/turbulent-boundary-layer interactions. The problem of compression corners at supersonic speeds was solved using the RPLUS2D code. To validate the RPLUS2D code for hypersonic speeds, it was applied to a realistic hypersonic inlet geometry. Both the Baldwin-Lomax and the Chien two-equation turbulence models were used. Computational results showed that the RPLUS2D code compared very well with experimentally obtained data for supersonic compression corner flows, except in the case of large separated flows resulting from the interactions between the shock wave and turbulent boundary layer. The computational results compared well with the experiment results in a hypersonic NASA P8 inlet case, with the Chien two-equation turbulence model performing better than the Baldwin-Lomax model. Kapoor, Kamlesh and Anderson, Bernhard H. and Shaw, Robert J. Glenn Research Center NASA-TM-106580, E-8840, NAS 1.15:106580 RTOP 537-02-23...
Download or read book An Experimental Investigation of Shock wave boundary layer Interaction Induced by Compression Corners Sharp Fins written by Ömer Haldun Ünalmış and published by . This book was released on 1989 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Shock Wave Interactions written by Konstantinos Kontis and published by Springer. This book was released on 2018-03-28 with total page 408 pages. Available in PDF, EPUB and Kindle. Book excerpt: This edited monograph contains the proceedings of the International Shock Interaction Symposium, which emerged as an heir to both the Mach Reflection and Shock Vortex Interaction Symposia. These scientific biannual meetings provide an ideal platform to expose new developments and discuss recent challenges in the field of shock wave interaction phenomena. The goal of the symposia is to offer a forum for international interaction between young and established scientists in the field of shock and blast wave interaction phenomena. The target audience of this book comprises primarily researchers and experts in the field of shock waves, but the book may also be beneficial for young scientists and graduate students alike.
Download or read book Hypersonic Boundary layer Stability Across a Compression Corner written by Hongwu Zhao and published by . This book was released on 2003 with total page 412 pages. Available in PDF, EPUB and Kindle. Book excerpt:
