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Separated and Vortical Flow in Aircraft Wing Aerodynamics - Basic Principles and Unit Problems (Hardcover, 1st ed. 2021)
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Separated and Vortical Flow in Aircraft Wing Aerodynamics - Basic Principles and Unit Problems (Hardcover, 1st ed. 2021)
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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.
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