Overview
- Presents the basic principles of separated and vortical flow, investigates the capabilities of numerical computation methods
- Introduces the concept of kinematically active and inactive vorticity content of a shear layer, and to the topology of skin-friction and velocity fields
- Investigates the evolution of the trailing vortex layer and the pair of trailing vortices of the wing of the NASA Common Research Model and other wings
- Illustrates the tip-vortex system with its minute non-linear lift, spans a bridge to the small aspect-ratio delta-type wing
- Treats the lee-side vortex systems of the Vortex-Flow Experiment and other delta-wing configurations, studies non-linear lift and vortex breakdown
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Table of contents (12 chapters)
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Front Matter
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Back Matter
Keywords
About this book
Fluid mechanical aspects of separated and vortical flow in aircraft wing aerodynamics are treated. The focus is on two wing classes: (1) large aspect-ratio wings and (2) small aspect-ratio delta-type wings. Aerodynamic design issues in general are not dealt with.
Discrete numerical simulation methods play a progressively larger role in aircraft design and development. Accordingly, in the introduction to the book the different mathematical models are considered, which underlie the aerodynamic computation methods (panel methods, RANS and scale-resolving methods). Special methods are the Euler methods, which as rather inexpensive methods embrace compressibility effects and also permit to describe lifting-wing flow.
Three main topics are treated:
1) Basic Principles are considered first: boundary-layer flow, vortex theory, the vorticity content of shear layers, Euler solutions for lifting wings, the Kutta condition in reality and the topology of skin-friction and velocity fields.
2) Unit Problems treat isolated flow phenomena of the two wing classes. Capabilities of panel and Euler methods are investigated. One Unit Problem is the flow past the wing of the NASA Common Research Model. Other Unit Problems concern the lee-side vortex system appearing at the Vortex-Flow Experiment 1 and 2 sharp- and blunt-edged delta configurations, at a delta wing with partly round leading edges, and also at the Blunt Delta Wing at hypersonic speed.
3) Selected Flow Problems of the two wing classes. In short sections practical design problems are discussed. The treatment of flow past fuselages, although desirable, was not possible in the frame of this book.Authors and Affiliations
Bibliographic Information
Book Title: Separated and Vortical Flow in Aircraft Wing Aerodynamics
Book Subtitle: Basic Principles and Unit Problems
Authors: Ernst Heinrich Hirschel, Arthur Rizzi, Christian Breitsamter, Werner Staudacher
DOI: https://doi.org/10.1007/978-3-662-61328-3
Publisher: Springer Berlin, Heidelberg
eBook Packages: Engineering, Engineering (R0)
Copyright Information: Springer-Verlag GmbH Germany, part of Springer Nature 2021
Hardcover ISBN: 978-3-662-61326-9Published: 05 October 2020
eBook ISBN: 978-3-662-61328-3Published: 04 October 2020
Edition Number: 1
Number of Pages: XV, 456
Number of Illustrations: 174 b/w illustrations, 111 illustrations in colour
Topics: Engineering Fluid Dynamics, Computational Intelligence