Physical Study of Shock-wave/boundary-layer Interaction Control in Transonic Flow PDF Download
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Author: Reynald Bur
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Reynald Bur
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Holger Babinsky
Publisher: Cambridge University Press
ISBN: 1139498649
Category : Technology & Engineering
Languages : en
Pages : 481
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Book Description
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.
Author: John Locke Gray
Publisher:
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Category :
Languages : en
Pages :
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Author: G. Lombardi
Publisher:
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Category :
Languages : en
Pages :
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Author: Piotr Doerffer
Publisher: Springer Science & Business Media
ISBN: 3642030041
Category : Technology & Engineering
Languages : en
Pages : 350
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This volume contains description of experimental and numerical results obtained in the UFAST project. The goal of the project was to generate experiment data bank providing unsteady characteristics of the shock boundary layer interaction. The experiments concerned basic-reference cases and the cases with application of flow control devices. Obtained new data bank have been used for the comparison with available simulation techniques, starting from RANS, through URANS, LES and hybrid RANS-LES methods. New understanding of flow physics as well as ability of different numerical methods in the prediction of such unsteady flow phenomena will be discussed.
Author: Deepak Om
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 358
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Author: Piotr Doerffer
Publisher: Springer Nature
ISBN: 3030474615
Category : Technology & Engineering
Languages : en
Pages : 540
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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.
Author: G. R. Inger
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages :
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A review is made of the existing knowledge about the interaction of impinging shock waves with laminar or turbulent boundary layers, to emphasize and illustrate that the relative degree of inviscid-dominated (solid wall-like) reflection behavior versus viscous-dominated (free surface-like) reflection is a major feature determining the disturbance flow pattern. This idea is then used to appraise existing transonic normal shock-boundary layer interaction experiments and establish an ordered relationship between them. As a result, it is shown that far from being unusual, a post-shock pocket of supersonic flow ("supersonic tongue") is in fact a common feature of all such interaction patterns, although its scale can change drastically with incident shock strength, Reynolds number and downstream conditions.
Author: Hideaki Ogawa
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Hans Wolfgang Liepmann
Publisher:
ISBN:
Category :
Languages : en
Pages : 637
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