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Book
Numerical methods for the computation of inviscid transonic flows with shock waves
Authors: ---
ISBN: 3528080779 Year: 1981 Publisher: Braunschweig : Vieweg,

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Book
Aircraft aerodynamic design with computational software
Authors: ---
ISBN: 1009038451 1009038257 113909467X Year: 2021 Publisher: Cambridge : Cambridge University Press,

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This modern text presents aerodynamic design of aircraft with realistic applications, using CFD software and guidance on its use. Tutorials, exercises, and mini-projects provided involve design of real aircraft, ranging from straight to swept to slender wings, from low speed to supersonic. Supported by online resources and supplements, this toolkit covers topics such as shape optimization to minimize drag and collaborative designing. Prepares seniors and first-year graduate students for design and analysis tasks in aerospace companies. In addition, it is a valuable resource for practicing engineers, aircraft designers, and entrepreneurial consultants.


Book
Numerical solutions of the Euler equations for steady flow problems
Authors: --- ---
ISBN: 3528076348 Year: 1992 Publisher: Braunschweig Vieweg

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Book
Separated and vortical flow in aircraft wing aerodynamics : basic principles and unit problems
Authors: --- --- ---
ISBN: 9783662613283 9783662613276 9783662613269 Year: 2021 Publisher: Berlin, Germany : Springer,

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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.


Digital
Separated and Vortical Flow in Aircraft Wing Aerodynamics : Basic Principles and Unit Problems
Authors: --- --- ---
ISBN: 9783662613283 9783662613276 9783662613269 Year: 2021 Publisher: Berlin, Heidelberg Springer

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Abstract

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.


Digital
100 Volumes of ‘Notes on Numerical Fluid Mechanics’ : 40 Years of Numerical Fluid Mechanics and Aerodynamics in Retrospect
Authors: --- --- --- --- --- et al.
ISBN: 9783540708056 Year: 2009 Publisher: Berlin, Heidelberg Springer Berlin Heidelberg


Digital
Numerical Simulation of Turbulent Flows and Noise Generation : Results of the DFG/CNRS Research Groups FOR 507 and FOR 508
Authors: --- --- --- --- --- et al.
ISBN: 9783540899563 Year: 2009 Publisher: Berlin, Heidelberg Springer Berlin Heidelberg


Digital
DESider – A European Effort on Hybrid RANS-LES Modelling : Results of the European-Union Funded Project, 2004–2007
Authors: --- --- --- --- --- et al.
ISBN: 9783540927730 Year: 2009 Publisher: Berlin, Heidelberg Springer Berlin Heidelberg


Digital
Hermann Schlichting – 100 Years : Scientific Colloquium Celebrating the Anniversary of His Birthday, Braunschweig, Germany 2007
Authors: --- --- --- --- --- et al.
ISBN: 9783540959984 Year: 2009 Publisher: Berlin, Heidelberg Springer Berlin Heidelberg

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