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Structure Of The Supersonic Turbulent Boundary Layer And Its Influence On Unsteady Separation
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Book Synopsis Structure of the supersonic turbulent boundary layer and its influence on unsteady separation by : Ömer Haldun Ünalmiş
Download or read book Structure of the supersonic turbulent boundary layer and its influence on unsteady separation written by Ömer Haldun Ünalmiş and published by . This book was released on 1995 with total page 510 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Book Synopsis Studies of the Mean and Unsteady Structure of Turbulent Boundary Layer Separation in Hypersonic Flow by : M. S. Holden
Download or read book Studies of the Mean and Unsteady Structure of Turbulent Boundary Layer Separation in Hypersonic Flow written by M. S. Holden and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis (U) Physical Models for Supersonic Turbulent Boundary Layer Structure by : Alexander J. Smits
Download or read book (U) Physical Models for Supersonic Turbulent Boundary Layer Structure written by Alexander J. Smits and published by . This book was released on 1989 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Organized Structures in a Supersonic Turbulent Boundary Layer by : Eric Francis Spina
Download or read book Organized Structures in a Supersonic Turbulent Boundary Layer written by Eric Francis Spina and published by . This book was released on 1988 with total page 466 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 Fundamental Aspects of the Structure of Supersonic Turbulent Boundary Layers by : Alexander J. Smits
Download or read book Fundamental Aspects of the Structure of Supersonic Turbulent Boundary Layers written by Alexander J. Smits and published by . This book was released on 1988 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Supersonic Boundary Layer Transition and Turbulent Structure by : Alexander J. Smits
Download or read book Investigation of Supersonic Boundary Layer Transition and Turbulent Structure written by Alexander J. Smits and published by . This book was released on 1990 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Numerical Investigation of Compressible Turbulent Boundary Layers by : Muhammad Farrukh Shahab
Download or read book Numerical Investigation of Compressible Turbulent Boundary Layers written by Muhammad Farrukh Shahab and published by LAP Lambert Academic Publishing. This book was released on 2012-02 with total page 228 pages. Available in PDF, EPUB and Kindle. Book excerpt: As a prerequisite for relevant model development and improvement of design methodologies for supersonic vehicles, this study aims at investigating the influence of wall heat-transfer and shock interaction on the turbulence structure of supersonic boundary layers. Incipient separation conditions and two different wall thermal boundary conditions (adiabatic and cold) are considered. The analysis focuses on the evolution of mean and turbulent flow properties along the interaction region and in the relaxation region downstream of the shock-system. The strong influence of the mean pressure gradient is quantified through the analysis of mean flow profiles and boundary layer integral parameters. The anisotropic amplification of turbulent quantities through the interaction region is characterized and the turbulent events associated with the modification of the turbulence structure of the perturbed boundary layer are identified. The mean and turbulent thermal fields are shown to be strongly modified by the wall cooling which significantly dampens more particularly the turbulent thermal quantities levels across the boundary layer.
Book Synopsis Separation measurements of supersonic turbulent boundary layers over compression corners by : Walter Bruce Gillette
Download or read book Separation measurements of supersonic turbulent boundary layers over compression corners written by Walter Bruce Gillette and published by . This book was released on 1967 with total page 111 pages. Available in PDF, EPUB and Kindle. Book excerpt: To the designer of modern high-speed aerospace vehicles, separation of the boundary layer before macroscopic surface features is an important problem. A typical feature of interest is a compression corner, or ramp. To aid in the development of comprehensive theories concerning boundary layer separation before a compression corner, a series of experimental investigations were conducted for the adiabatic flow of a supersonic compressible gas over a compression corner. Tests were conducted at free-stream Mach Numbers of 2.00 to 4.00 in increments of 0.50, at flat plate Reynolds Numbers of 0.75 x 10 to the 7th and 1.5 x 10 to the 7th, and for compression angles of 10.3 deg, 20.1 deg, 30.5 deg, and 39.9 deg. Static pressure surveys of the flow ahead of and over the compression corner were made. These measurements were supplemented by high-speed schlieren photographs and shadowgraphs. The separation of the turbulent compressible boundary layer was found to have strong dependence on both the Mach Number and the Reynolds Number. For Mach Numbers less than 3.00, the separation distance ahead of the compression corner decreased with increasing Mach Number. For Mach Numbers of 3.50 and 4.00, the separation distance increased with Mach Number. At all Mach Numbers, an increase in Reynolds Number increased the separation distance. The Reynolds Number influence was greater at the higher Reynolds Numbers. Unsteadiness in the separation geometry occurred for separation distances greater than six or eight boundary layer thicknesses. The separation was found to result from a free interaction of the flow phenomena involved. (Author).
Book Synopsis The effects of incoming boundary layer thickness on unsteady shock-induced turbulent separations induced by cylinders by : Douglas Robert Smith
Download or read book The effects of incoming boundary layer thickness on unsteady shock-induced turbulent separations induced by cylinders written by Douglas Robert Smith and published by . This book was released on 1987 with total page 208 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wall pressure fluctuations were measured under the unsteady separation shock/turbulent boundary layer interaction induced by unswept circular cylinders to determine the role of the incoming turbulent boundary layer thickness on the shock motion. Measurements were taken in a high Reynolds number, Mach 5 flow in the turbulent boundary layer developed on the wind tunnel floor. The wall temperature was adiabatic. High frequency response, miniature pressure transducers were mounted flush with the tunnel floor to measure the pressure fluctuations caused by the shock motion. A conditional sampling algorithm was used to separate the pressure fluctuations due to the shock motion from those fluctuations associated with the incoming and downstream turbulent boundary layer. Standard time series analysis techniques were used to analyze the data. Results show that the turbulent boundary layer has only second order effects on the frequency of the separation shock. Shock frequencies are at least one order of magnitude less than the large eddy frequency of the turbulent boundary layer. The low frequency pressure fluctuations of the separated region are within the same frequency range as the shock frequencies. These pressure fluctuations are a possible cause of the shock motion and warrant further investigation. Keywords: Hypersonic flow separation; Unsteady flow. Theses (EDC).
Book Synopsis Application of an Interacting Boundary Layer Model to the Supersonic Turbulent Separation Problem by : M. J. Werle
Download or read book Application of an Interacting Boundary Layer Model to the Supersonic Turbulent Separation Problem written by M. J. Werle and published by . This book was released on 1976 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Numerical solutions to the supersonic interacting turbulent boundary layer equations are obtained for ramp induced separation problems. The method used is the alternating direction implicit scheme wherein a time-like relaxation process is followed to a sought after steady state. The turbulent structure of the flow is modeled with an eddy viscosity approach using both the equilibrium and relaxation models. Detailed comparisons of the present solution with experimental data and available Navier Stokes solutions show that this approach fails to predict the correct extent of upstream influence. The deficiency is traced to the absence of an imbedded shock wave in the interacting boundary layer model of the viscous region. (Author).
Book Synopsis Expansion Effects on Supersonic Turbulent Boundary Layers by :
Download or read book Expansion Effects on Supersonic Turbulent Boundary Layers written by and published by . This book was released on 1994 with total page 191 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of various expansion regions on the large scale structure of a Mach 3 fully-developed-turbulent boundary layer are investigated. Five cases are studied: 7 deg and 14 deg centered expansions, 7 deg and 14 deg gradual expansions, and the flat plate. Multi-point surface pressure measurements, filtered Rayleigh scattering visualizations, and double-pulse visualizations were employed. Plan view images of the flat plate boundary layer reveal the presence of structures of a very large streamwise, and limited spanwise, extent. These structures were found well above the inner layer, nominally at n/delta = 0.5-1.0. The structures were also found in the expanded boundary layers. Across the expansion, the large scale structures of the outer layer undergo an increase in scale and structure angle. The small scale turbulent motions of the incoming boundary layer are quenched by the expansion, while the large scale structures respond more gradually. Convection velocities from the pressure correlations are reasonable in the incoming boundary layer, but unreasonably high in the expanded boundary layers. Convection velocities from correlations of double-pulse images appear reasonable. The discrepancy between the two results suggests the relationship between the large scale structures and the convecting pressure field is severely altered by the expansions.
Book Synopsis Investigation of Supersonic Turbulent Boundary-layer Separation on a Compression Ramp by an Integral Method by :
Download or read book Investigation of Supersonic Turbulent Boundary-layer Separation on a Compression Ramp by an Integral Method written by and published by . This book was released on 1977 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Incipient Separation of a Supersonic, Turbulent Boundary Layer Including Effects of Heat Transfer by : John Carrol Frishett
Download or read book Incipient Separation of a Supersonic, Turbulent Boundary Layer Including Effects of Heat Transfer written by John Carrol Frishett and published by . This book was released on 1971 with total page 272 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 686 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 The prediction of free separation of a supersonic turbulent boundary layer including effects of upstream flow history by : Donald Albert Hall
Download or read book The prediction of free separation of a supersonic turbulent boundary layer including effects of upstream flow history written by Donald Albert Hall and published by . This book was released on 1971 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt:
