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Numerical Simulation Of Turbulent Shock Boundary Layer Interactions In Hypersonic Flows
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Book Synopsis Numerical Simulation of Turbulent Shock/boundary-layer Interactions in Hypersonic Flows by : Turan Coratekin
Download or read book Numerical Simulation of Turbulent Shock/boundary-layer Interactions in Hypersonic Flows written by Turan Coratekin and published by . This book was released on 2000 with total page 96 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 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 Hypersonic Shock Wave Turbulent Boundary Layers by : Doyle Knight
Download or read book Hypersonic Shock Wave Turbulent Boundary Layers written by Doyle Knight and published by . This book was released on 2023 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hypersonic turbulent boundary layers are a fundamental phenomenon in high-speed flight. The interaction of shock waves with hypersonic turbulent boundary layers has a critical impact on vehicle aerothermodynamic loading including surface heat transfer, pressure and skin friction. This book provides a comprehensive exposition of hypersonic turbulent boundary layers, including the fundamental mathematical theory, structure of equilibrium boundary layers, and extensive surveys of Direct Numerical Simulation (DNS), Large Eddy Simulation (LES) and experiments. It also provides a roadmap for both future experiments and DNS and LES simulations. Descriptions of hypersonic ground test facilities is included as an appendix. As a research and reference text, this book would appeal to graduate students and researchers in hypersonics and could be the basis for professional training courses.
Book Synopsis Documentation of Two- and Three-dimensional Hypersonic Shock Wave/turbulent Boundary Layer Interaction Flows by : Marvin I. Kussoy
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:
Book Synopsis Interactions Entre Ondes de Choc Et Couches Limites Dans Les Ecoulements Supersoniques Et Hypersoniques by :
Download or read book Interactions Entre Ondes de Choc Et Couches Limites Dans Les Ecoulements Supersoniques Et Hypersoniques written by and published by . This book was released on 1993 with total page 298 pages. Available in PDF, EPUB and Kindle. Book excerpt: "Shock-wave/boundary-layer interactions continue to be ubiquitous phenomena in supersonic and hypersonic aerodynamics, and their importance is often critical as, for example, for hypersonic controls and for air intakes in general. This is the reason for the continuous research efforts in this field, aiming at developing reliable methodologies for future vehicle design. Results from these programmes have been reported. The present course reviews the recent progress in this field. In particular, a large part of the course is devoted to swept interactions, both laminar and turbulent, including a discussion of the following topics: (1) The flowfield structure; (2) The scaling and similarity laws; (3) The effect of shock strength on flow features; (4) The effect of shock generator geometry for a given shock strength; (5) Experimental techniques, in particular optical techniques, for the investigation of swept interactions; and (6) Contributions of numerical simulations to the understanding of swept interactions. A limiting factor in the understanding and ability to predict shock wave/boundary-layer interactions is a good knowledge of turbulence behavior. A lecture is devoted specifically to hypersonic interactions."--DTIC.
Book Synopsis Numerical Simulation of Viscous Shock Layer Flows by : Y.P. Golovachov
Download or read book Numerical Simulation of Viscous Shock Layer Flows written by Y.P. Golovachov and published by Springer Science & Business Media. This book was released on 2013-03-09 with total page 359 pages. Available in PDF, EPUB and Kindle. Book excerpt: The book is concerned with mathematical modelling of supersonic and hyper sonic flows about bodies. Permanent interest in this topic is stimulated, first of all, by aviation and aerospace engineering. The designing of aircraft and space vehicles requires a more precise prediction of the aerodynamic and heat transfer characteristics. Together with broadening of the flight condition range, this makes it necessary to take into account a number of gas dynamic and physical effects caused by rarefaction, viscous-inviscid interaction, separation, various physical and chemical processes induced by gas heating in the intensive bow shock wave. The flow field around a body moving at supersonic speed can be divided into three parts, namely, shock layer, near wake including base flow, and far wake. The shock layer flow is bounded by the bow shock wave and the front and lat eral parts of the body surface. A conventional approach to calculation of shock layer flows consists in a successive solution of the inviscid gas and boundary layer equations. When the afore-mentioned effects become important, implementation of these models meets difficulties or even becomes impossible. In this case, one has to use a more general approach based on the viscous shock layer concept.
Book Synopsis Numerical Simulation of 3-D Shock Wave Turbulent Boundary Layer Interaction Using a Two Equation Model of Turbulence by : Marianna Gnedin
Download or read book Numerical Simulation of 3-D Shock Wave Turbulent Boundary Layer Interaction Using a Two Equation Model of Turbulence written by Marianna Gnedin and published by . This book was released on 1996 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Understanding and Predicting Shockwave and Turbulent Boundary Layer Interactions by : M. Pino Martin
Download or read book Understanding and Predicting Shockwave and Turbulent Boundary Layer Interactions written by M. Pino Martin and published by . This book was released on 2009 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Shockwave and turbulent boundary layer interactions produce intense localized pressure loads and heating rates that can have a dramatic influence on the drag and heating experienced by a high-speed vehicle, and can significantly impact fuel mixing and combustion in propulsion systems. The lack of standardized and traceable databases prevents the calibration of computational fluid dynamic models to accurately represent these critical flow phenomena. In this work we accomplished the development and validation against experiments at the same flow and boundary conditions of direct numerical simulations of shock and turbulent boundary layer interactions. We pioneered the development of a unique numerical capability that allows the accurate and detailed three-dimensional turbulence data at a reasonable turn-around time. In turn, parametric studies of fundamental flow physics are feasible, for the first time. By accurate, it is meant that the numerical uncertainty is within the experimental error.
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781792705748 Total Pages :30 pages Book Rating :4.7/5 (57 download)
Book Synopsis Numerical Simulation of Supersonic Compression Corners and Hypersonic Inlet Flows Using the Rplus2d Code by : National Aeronautics and Space Adm Nasa
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...
Book Synopsis Numerical Simulation of Shock/turbulent Boundary Layer Interactions Over 2-D Compression Corners by : Miguel Visbal
Download or read book Numerical Simulation of Shock/turbulent Boundary Layer Interactions Over 2-D Compression Corners written by Miguel Visbal and published by . This book was released on 1983 with total page 334 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Numerical Simulation of Turbulent Shock-Induced Separated Flows by : Afaque Shams
Download or read book Numerical Simulation of Turbulent Shock-Induced Separated Flows written by Afaque Shams and published by LAP Lambert Academic Publishing. This book was released on 2011-03 with total page 248 pages. Available in PDF, EPUB and Kindle. Book excerpt: Shock-induced flow separation and its subsequent reattachment are encountered in many configurations, such as supersonic inlets or rocket nozzles. These phenomena involve complex interactions of boundary layers with compression or expansion waves and exhibit a low-frequency unsteady behaviour which still requires a clear explanation. This study aims at better identifying the physical mechanisms which drive the global structure of these flows and suggesting improved numerical tools in order to predict these more accurately. The appearance of free and restricted separations in supersonic separated jets is more particularly investigated. Various hypotheses are tested to explain the evolution of the associated unsteady asymmetric wall pressure field in function of the nozzle pressure ratio. New numerical strategies are proposed and lead to identify more accurately the appearance of free and restricted separations and the time-varying morphology of the flow during the transition process. Possible origins of side-load activities are extensively investigated by performing the azimuthal expansion of wall pressure field.
Book Synopsis Numerical Simulation of Hypersonic Oblique Shock-wave/laminar Boundary-layer Interaction with Shock Induced Combustion by : Chen Chuck
Download or read book Numerical Simulation of Hypersonic Oblique Shock-wave/laminar Boundary-layer Interaction with Shock Induced Combustion written by Chen Chuck and published by . This book was released on 1990 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Turbulence Modeling for Hypersonic Flows by : Joseph G. Marvin
Download or read book Turbulence Modeling for Hypersonic Flows written by Joseph G. Marvin and published by . This book was released on 1989 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Numerical Studies of Low-Density Two-Dimensional Hypersonic Flows by Using the Navier-Stokes and Burnett Equations with Nonequilibrium Real Gas Effects by :
Download or read book Numerical Studies of Low-Density Two-Dimensional Hypersonic Flows by Using the Navier-Stokes and Burnett Equations with Nonequilibrium Real Gas Effects written by and published by . This book was released on 1997 with total page 33 pages. Available in PDF, EPUB and Kindle. Book excerpt: The goal of this research is to study the laminar turbulent transition and other transient flow phenomena of 3-D chemically reacting hypersonic boundary layers by direct numerical simulation (DNS) and by linear stability analysis. The research in the report period was focused on developing new numerical methods for such studies and studying several fundamental transient hypersonic flow phenomena. First, several new efficient and high-order accurate numerical methods for DNS of 3-D hypersonic reacting boundary layers and for computing unsteady hypersonic flows with complex shock interactions were developed. These new methods were developed in order to overcome difficulties associated with the direct numerical simulation of hypersonic flows. Second, several studies on the stability phenomena of hypersonic boundary layers over blunt leading edges both by direct numerical simulation and by linear stability analyses were performed. Also completed were extensive numerical studies on real gas effects on a steady shock/boundary layer interaction and a self-sustained unsteady shock-shock interference heating flows. Third, the effects of using Burnett equations for rarefied hypersonic flow computations were investigated. With the completion of the bulk of work on the development of new numerical methods for complex hypersonic flow simulation, the DNS studies are currently being extended to 3-D hypersonic boundary layer transition over elliptic cross section cones.
Book Synopsis Evaluation of Various Turbulence Models for Shock-wave Boundary Layer Interaction Flows by : Francis Kofi Acquaye
Download or read book Evaluation of Various Turbulence Models for Shock-wave Boundary Layer Interaction Flows written by Francis Kofi Acquaye and published by . This book was released on 2016 with total page 53 pages. Available in PDF, EPUB and Kindle. Book excerpt: Despite the modeling capabilities of current computational fluid dynamics (CFD), there still exist problems and inconsistencies in simulating fluid flow in certain flow regimes. Most difficult are the high-speed transonic, supersonic and hypersonic wall-bounded turbulent flows with small or massive regions of separation. To address the problem of the lack of computational accuracy in turbulence modeling, NASA has established the Turbulence Modeling Resource (TMR) website and has issued the NASA 40% Challenge. The aim of this challenge is to identify and improve/develop turbulence and transition models as well as numerical techniques to achieve a 40% reduction in the predictive error in computation of benchmark test cases for turbulent flows. One of the phenomena of considerable interest in the 40% Challenge is the shock-wave boundary layer interaction (SWBLI) that occurs on aircraft surfaces at transonic and supersonic speeds and on space vehicles at hypersonic speeds. The correct modeling of shock-waves is complex enough, but the occurrence of SWBLI adds to the complexity by promoting flow separation, heat transfer, and pressure gradients on the surface. SWBLI may occur in both the external and internal flow path of air and space vehicles; therefore, it is important to accurately predict this phenomenon to improve the design of aircraft and space vehicles. The majority of CFD codes utilize the Reynolds Averaged Navier-Stokes (RANS) equations and employ various turbulence models. The most common among these turbulent models are the one-equation Spalart-Allmaras (SA) model and the two-equation Shear Stress Transport (SST) k-[omega] model. In recent years the CFD community has, in greater number, also started to adopt Large-Eddy Simulation (LES), Direct Numerical Simulation (DNS), and hybrid RANS-LES approaches for improving the accuracy of simulations. However currently, solving the RANS equations with eddy-viscosity turbulence models remains the most commonly used simulation technique in industrial applications. In this research, the one-equation Wray-Agarwal (WA), SA, and SST k-[omega] turbulence models are used to simulate supersonic flows in a 2D compression corner at angles of 8° and 16°, a partial axisymmetric flare of 20°, a full-body conical axisymmetric flare of 20°, and an impinging shock over a flat plate at 6°, 10°, and 14°. The ANSYS Fluent and OpenFOAM flow solvers are employed. Inflow boundary conditions and mesh sensitivity are examined to ensure the grid independence of computed solutions. For each of the three turbulence models, heat transfer, surface pressure, skin friction, and velocity profiles are compared with the available experimental data. It is found that the results from the WA model are in similar or better agreement with the experimental data compared to the SA and SST k-[omega] models for the majority of cases considered.
Book Synopsis Numerical Computations of Turbulence Amplification in Shock Wave Interactions by : Thomas A. Zang
Download or read book Numerical Computations of Turbulence Amplification in Shock Wave Interactions written by Thomas A. Zang and published by . This book was released on 1983 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
