Transition Location Effect on Shock Wave Boundary Layer Interaction
Language: English
Published by Springer International Publishing, 2020
Series: Book 27 of 30 - Notes on Numerical Fluid Mechanics and Multidisciplinary Design
- Hardcover
- New
Condition: New
£ 118.87
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Dieser Artikel ist ein Print on Demand Artikel und wird nach Ihrer Bestellung fuer Sie gedruckt. Presents advanced methods for improving flow performance Fosters a better understanding the consequences of laminar interactionsShows how CFD can be used to predict complex flow phenomenaThis book presents experimental and num.
Seller Inventory # 448682951
- Title
- Transition Location Effect on Shock Wave Boundary Layer Interaction
- Author
- Doerffer, Piotr|Flaszynski, Pawel|Dussauge, Jean-Paul|Babinsky, Holger|Grothe, Patrick|Petersen, Anna|Billard, Flavien
- Publisher
- Springer International Publishing
- Publication year
- 2020
- Condition
- New
- Binding
- Gebunden
- Language
- English
- ISBN 10
- 3030474607
- ISBN 13
- 9783030474607
- Series
- Book 27 of 30: Notes on Numerical Fluid Mechanics and Multidisciplinary Design
- Seller catalogs
- Mathematik/Naturwissenschaften/Technik/Medizin
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.
"Synopsis" may belong to another edition of this title.
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.
"About the title" may belong to another edition of this title.
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