Interaction Between a Normal Shock Wave and a Turbulent Boundary Layer at High Transonic Speeds. Part 1: Pressure Distribution. Part 2: Wall Shear Stress. Part 3: Simplified Formulas for the Prediction of Surface Pressures and Skin Friction PDF Download
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Author:
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ISBN:
Category :
Languages : en
Pages : 144
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 144
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 1280
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Book Description
Author: Thomas Charles Adamson
Publisher:
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Category : Shock waves
Languages : en
Pages : 152
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Book Description
Author: M. S. Liou
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Category :
Languages : en
Pages :
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ISBN:
Category : Science
Languages : en
Pages : 246
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Category : Government reports announcements & index
Languages : en
Pages : 988
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Book Description
Author: George G. Mateer
Publisher:
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Category :
Languages : en
Pages : 14
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Book Description
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.
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Category : Shear flow
Languages : en
Pages : 466
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Book Description
Author: R. E. Melnik
Publisher:
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Category :
Languages : en
Pages : 34
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Book Description
The method of matched asymptotic expansions is used to analyze the interaction of a normal shock wave with an unseparated turbulent boundary layer on a flat surface at transonic speeds. The theory leads to a three-layer description of the interaction in the double limit of Reynolds number approaching infinity and Mach number approaching unity. The interaction involves an outer, inviscid rotational layer, a constant shear-stress wall layer, and a blending region between them.
