Separated and vortical flow in aircraft wing aerodynamics : basic principles and unit problems / Ernst Heinrich Hirschel, Arthur Rizzi, Christian Breitsamter, Werner Staudacher.
Hirschel, Ernst-Heinrich.; Rizzi, Arthur.; Breitsamter, Christian, 1962-; Staudacher, Werner.
2021
TL545
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Title Separated and vortical flow in aircraft wing aerodynamics : basic principles and unit problems / Ernst Heinrich Hirschel, Arthur Rizzi, Christian Breitsamter, Werner Staudacher.
ISBN 9783662613283 (electronic bk.)
366261328X (electronic bk.)
3662613263
9783662613269
DOI https://doi.org/10.1007/978-3-662-61328-3
Publication Details Berlin, Germany : Springer, 2021.
Language English
Description 1 online resource
Item Number 10.1007/978-3-662-61328-3 doi
Call Number TL545
Dewey Decimal Classification 629.13/23
Summary 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. The concept of the kinematically active and inactive vorticity content of shear layers gives insight into many flow phenomena, but also, with the second break of symmetry--the first one is due to the Kutta condition--an explanation of lifting-wing flow fields. The prerequisite is an extended definition of separation: "flow-off separation" at sharp trailing edges of class (1) wings and at sharp leading edges of class (2) wings. The vorticity-content concept, with a compatibility condition for flow-off separation at sharp edges, permits to understand the properties of the evolving trailing vortex layer and the resulting pair of trailing vortices of class (1) wings. The concept also shows that Euler methods at sharp delta or strake leading edges of class (2) wings can give reliable results. 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
Bibliography, etc. Note Includes bibliographical references and indexes.
Access Note Access limited to authorized users.
Digital File Characteristics text file
PDF
Source of Description Online resource; title from PDF title page (SpringerLink, viewed November 24, 2020).
Added Author Hirschel, Ernst-Heinrich.
Rizzi, Arthur.
Breitsamter, Christian, 1962-
Staudacher, Werner.
Available in Other Form Separated and vortical flow in aircraft wing aerodynamics.
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Introduction
Separation: Some Relevant Boundary-Layer Properties, Interaction Issues, and Drag
Elements of Vortex Theory
The Local Vorticity Content of a Shear Layer
The Matter of Discrete Euler Solutions for Lifting Wings
About the Kutta Condition
Topology of Skin-Friction and Velocity Fields
Large Aspect-Ratio Wing Flow
Particular Flow Problems of Large Aspect-Ratio Wings
Small Aspect-Ratio Delta-Type Wing Flow
Selected Flow Problems of Small Aspect-Ratio Delta-Type Wings
Solutions of the Problems.

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