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001432084 001__ 1432084
001432084 003__ OCoLC
001432084 005__ 20230309003422.0
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001432084 019__ $$a1204152593$$a1228844503$$a1241066398$$a1241531821
001432084 020__ $$a9783662613283$$q(electronic bk.)
001432084 020__ $$a366261328X$$q(electronic bk.)
001432084 020__ $$z3662613263
001432084 020__ $$z9783662613269
001432084 0247_ $$a10.1007/978-3-662-61328-3$$2doi
001432084 035__ $$aSP(OCoLC)1199128664
001432084 040__ $$aYDX$$beng$$epn$$cYDX$$dGW5XE$$dOCLCF$$dOCLCO$$dESU$$dSFB$$dUPM$$dDKU$$dOCLCQ$$dOCLCO$$dOCL$$dOCLCQ
001432084 049__ $$aISEA
001432084 050_4 $$aTL545
001432084 08204 $$a629.13/23$$223
001432084 24500 $$aSeparated and vortical flow in aircraft wing aerodynamics :$$bbasic principles and unit problems /$$cErnst Heinrich Hirschel, Arthur Rizzi, Christian Breitsamter, Werner Staudacher.
001432084 260__ $$aBerlin, Germany :$$bSpringer,$$c2021.
001432084 300__ $$a1 online resource
001432084 336__ $$atext$$btxt$$2rdacontent
001432084 337__ $$acomputer$$bc$$2rdamedia
001432084 338__ $$aonline resource$$bcr$$2rdacarrier
001432084 347__ $$atext file
001432084 347__ $$bPDF
001432084 504__ $$aIncludes bibliographical references and indexes.
001432084 5050_ $$aIntroduction -- 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.
001432084 506__ $$aAccess limited to authorized users.
001432084 520__ $$aFluid 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
001432084 588__ $$aOnline resource; title from PDF title page (SpringerLink, viewed November 24, 2020).
001432084 650_0 $$aVortex-motion.
001432084 650_0 $$aVortex-motion$$xMathematical models.
001432084 650_0 $$aAirplanes$$xWings$$xMathematical models.
001432084 650_0 $$aEddies.
001432084 650_6 $$aTourbillons (Mécanique des fluides)
001432084 650_6 $$aTourbillons (Mécanique des fluides)$$xModèles mathématiques.
001432084 650_6 $$aAvions$$xAiles$$xModèles mathématiques.
001432084 655_0 $$aElectronic books.
001432084 7001_ $$aHirschel, Ernst-Heinrich.
001432084 7001_ $$aRizzi, Arthur.
001432084 7001_ $$aBreitsamter, Christian,$$d1962-
001432084 7001_ $$aStaudacher, Werner.
001432084 77608 $$iPrint version:$$tSeparated and vortical flow in aircraft wing aerodynamics.$$dBerlin, Germany : Springer, 2021$$z3662613263$$z9783662613269$$w(OCoLC)1141124574
001432084 852__ $$bebk
001432084 85640 $$3Springer Nature$$uhttps://univsouthin.idm.oclc.org/login?url=https://link.springer.com/10.1007/978-3-662-61328-3$$zOnline Access$$91397441.1
001432084 909CO $$ooai:library.usi.edu:1432084$$pGLOBAL_SET
001432084 980__ $$aBIB
001432084 980__ $$aEBOOK
001432084 982__ $$aEbook
001432084 983__ $$aOnline
001432084 994__ $$a92$$bISE