Transition Location Effect on Shock Wave Boundary Layer Interaction: Experimental and Numerical Findings from the TFAST Project: 144 (Notes on ... Mechanics and Multidisciplinary Design, 144) - Image 1

£109.08

Springer Transition Location Effect on Shock Wave Boundary Layer Interaction: Experimental and Numerical Findings from the TFAST Project: 144 (Notes on ... Mechanics and Multidisciplinary Design, 144)

Name: Transition Location Effect on Shock Wave Boundary Layer Interaction: Experimental and Numerical Findings from the TFAST Project: 144 (Notes on ... Mechanics and Multidisciplinary Design, 144)
Brand: Springer
Price: 109.08 GBP
Availability: InStock

Interface Design

About as cheap as it gets. The only time it was cheaper was 3 months ago.

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Description

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. From the Back Cover 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.

Product Specifications

Brand: Springer
Format: hardcover
ASIN: 3030474607
Category: Books > Subjects > Computing & Internet > Programming > Interface Design
Domain: Amazon UK
Release Date: 31 July 2020
Listed Since: 03 April 2020

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Springer Transition Location Effect on Shock Wave Boundary Layer Interaction: Experimental and Numerical Findings from the TFAST Project: 144 (Notes on ... Mechanics and Multidisciplinary Design, 144)

About as cheap as it gets. The only time it was cheaper was 3 months ago.

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