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Incipient Separation Of A Turbulent Boundary Layer At High Reynolds Number In Two Dimensional Supersonic Flow Over A Compression Corner
Download Incipient Separation Of A Turbulent Boundary Layer At High Reynolds Number In Two Dimensional Supersonic Flow Over A Compression Corner full books in PDF, epub, and Kindle. Read online Incipient Separation Of A Turbulent Boundary Layer At High Reynolds Number In Two Dimensional Supersonic Flow Over A Compression Corner ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Incipient Separation of a Turbulent Boundary Layer at High Reynolds Number in Two- Dimensional Supersonic Flow Over a Compression Corner by :
Download or read book Incipient Separation of a Turbulent Boundary Layer at High Reynolds Number in Two- Dimensional Supersonic Flow Over a Compression Corner written by and published by . This book was released on 1969 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Two-dimensional Compression Corner and Planar Shock Wave Interactions with a Supersonic, Turbulent Boundary Layer by : C. Herbert Law
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:
Book Synopsis Experimental Study on High Subsonic Turbulent Flow Incipient Separation by : Jain-Ming Wu
Download or read book Experimental Study on High Subsonic Turbulent Flow Incipient Separation written by Jain-Ming Wu and published by . This book was released on 1976 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: For flow over a two-dimensional ramp compression corner case, an experimental investigation to determine the incipient separation was carried out at Mach numbers between 0.55 and 0.9 and Reynolds numbers (based on undisturbed boundary layer thickness) between 350,000 and 690,000. Detailed surface pressure, pitot traversing and oil flow data were obtained for each ramp angle case. Two-dimensionality of the ramp compression corners was verified by the surface oil flow. A major finding of this study is that the incipient separation ramp angle is relatively independent of Mach number and Reynolds number within the range studied. The incipient separation ramp angle was found to be about 22.5 degrees.
Book Synopsis Research on Supersonic Turbulent Separated and Reattached Flows by : Seymour M. Bogdonoff
Download or read book Research on Supersonic Turbulent Separated and Reattached Flows written by Seymour M. Bogdonoff and published by . This book was released on 1975 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt: Basic research programs are reported with fundamental applications to supersonic flight. The experimental studies made use of the unique capabilities of the high Reynolds number Mach 3 facility. The experimental programs concentrated on phenomena associated with incipient separation and separation of turbulent boundary layers over a large Reynolds number range. The reattachment phenomena of a shear layer was also studied in great depth.
Book Synopsis Turbulent Boundary-layer Separation Induced by Flares on Cylinders at Zero Angle of Attack by : Donald M. Kuehn
Download or read book Turbulent Boundary-layer Separation Induced by Flares on Cylinders at Zero Angle of Attack written by Donald M. Kuehn and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Separation caused by the pressure rise induced by flares has been experimentally investigated in the Mach number range of 1.5 to 5.0 and in the Reynolds number range (based on boundary-layer thickness) of 1.5X104 to 12X104. The purpose of the investigation was to determine the model geometry and flow conditions for which separation can be expected for a turbulent boundary layer of zero pressure gradient on the cylinder approaching the flare. Comparisons are made of the boundary-layer-separation characteristics of these three-dimensional flares with two-dimensional separation results from a previous investigation.
Download or read book NASA Technical Report written by and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scramjet Propulsion by : E. T. Curran
Download or read book Scramjet Propulsion written by E. T. Curran and published by AIAA. This book was released on 2001 with total page 1354 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research Memorandum by : United States. National Advisory Committee for Aeronautics
Download or read book Research Memorandum written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1956 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1979 with total page 738 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Book Synopsis Separated Flows and Jets by : Victor V. Kozlov
Download or read book Separated Flows and Jets written by Victor V. Kozlov and published by Springer Science & Business Media. This book was released on 2012-12-06 with total page 907 pages. Available in PDF, EPUB and Kindle. Book excerpt: Separated flows and jets are closely linked in a variety of applications. They are of great importance in various fields of fluid mechanics including vehicle efficiency, technical branches concerned with gas/liquid flows, atmospheric effects on various constructions, etc. Knowledge of the physics of separated flows and jets and the development of reliable control techniques are prerequisite for future progress in the field. These aspects were in focus during the IUTAM-Symposium which was held in Novosibirsk, 9-13 July, 1990. This volume contains a selection of papers presenting recent results of theoretical and numerical studies as well as experimental work on separated flows and jets. The topics include sub- and supersonic, laminar and turbulent separation as well as organized structures in separated flows and jets. The reader will find here the state of the art and major trends for research in this field of aero-hydrodynamics.
Book Synopsis Shock Wave-Boundary-Layer Interactions by : Holger Babinsky
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 ASME Technical Papers written by and published by . This book was released on with total page 490 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1973 with total page 568 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Turbulent Boundary-layer Temperature Recovery Factors in Two-dimensional Supersonic Flow by : Maurice Tucker
Download or read book Turbulent Boundary-layer Temperature Recovery Factors in Two-dimensional Supersonic Flow written by Maurice Tucker and published by . This book was released on 1951 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analytical method is presented for obtaining turbulent temperature recovery factors for a thermally insulated surface in supersonic flow. The method is an extension of Squire's analysis for incompressible flow. The boundary layer velocity profile is represented by a power law and a similarity is postulated for squared-velocity the static-temperature-difference profiles.
Book Synopsis Turbulent Boundary Layer Separation at Mach 12 by : C. Appels
Download or read book Turbulent Boundary Layer Separation at Mach 12 written by C. Appels and published by . This book was released on 1973 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Turbulent Shear Layers in Supersonic Flow by : Alexander J. Smits
Download or read book Turbulent Shear Layers in Supersonic Flow written by Alexander J. Smits and published by Springer Science & Business Media. This book was released on 2006-05-11 with total page 418 pages. Available in PDF, EPUB and Kindle. Book excerpt: A good understanding of turbulent compressible flows is essential to the design and operation of high-speed vehicles. Such flows occur, for example, in the external flow over the surfaces of supersonic aircraft, and in the internal flow through the engines. Our ability to predict the aerodynamic lift, drag, propulsion and maneuverability of high-speed vehicles is crucially dependent on our knowledge of turbulent shear layers, and our understanding of their behavior in the presence of shock waves and regions of changing pressure. Turbulent Shear Layers in Supersonic Flow provides a comprehensive introduction to the field, and helps provide a basis for future work in this area. Wherever possible we use the available experimental work, and the results from numerical simulations to illustrate and develop a physical understanding of turbulent compressible flows.
Book Synopsis Interacting Supersonic Turbulent Boundary Layers Over a Two-dimensional Protuberance by : Arnold Polak
Download or read book Interacting Supersonic Turbulent Boundary Layers Over a Two-dimensional Protuberance written by Arnold Polak and published by . This book was released on 1974 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report presents a numerical study of attached interacting supersonic turbulent boundary layers over a two-dimensional protuberance. Results are presented in terms of surface pressure, heat transfer and skin-friction distributions. These results indicate a strong effect of the size of the protuberance, Mach number, but a weak effect of Reynolds number and the ratio of wall-to-recovery temperature. The peak heating rates from a set of test cases compare well to a semi-empirical prediction method. In contradistinction to the laminar case, the turbulent recovery zone downstream of the protuberance is very short. (Author).
