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Transition Location Effect on Shock Wave Boundary Layer Interaction

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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.

Availability
Inventory Code Barcode Call Number Location Status
1908001363EB0001969532.05 TraCentral Library (OPAC)Available
Detail Information
Series Title
Notes on Numerical Fluid Mechanics and Multidisciplinary Design
Call Number
532.05 Tra
Publisher
Switzerland : Springer Cham.,
Collation
VIII, 540p.:Ill
Language
English
ISBN/ISSN
978-3-030-47461-4
Classification
532.05
Content Type
Ebook
Media Type
-
Carrier Type
online resource
Edition
1
Subject(s)
Shock waves
Specific Detail Info
-
Statement of Responsibility
Other version/related

No other version available

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