Separated and Vortical Flow in Aircraft Wing Aerodynamics

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Basic Principles and Unit Problems

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Basic Principles and Unit Problems

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 Common Research Model. Demonstrated too is that a tip-vortex system leads to a minute non-linear lift and that a bridge can be spanned over to class (2) wings. Other Unit Problems concern the lee-side vortex system appearing on class (2) wings with sharp and fully or partly round leading edges, and also that on a blunt-edged configuration 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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اشاعه ی کودک آزاری
سایر موارد

بستن

فرمت کتاب

ebook

زبان

english

تاریخ انتشار

2020

نویسنده

Werner Staudacher

ناشر

Springer

شابک

9783662613269

20,000 تومان

خرید کتاب مطالعه نمونه درخواست ترجمه کتاب

خرید کتاب Separated and Vortical Flow in Aircraft Wing Aerodynamics

Separated and Vortical Flow in Aircraft Wing Aerodynamics

گزارش تخلف

فرمت کتاب

ebook

زبان

english

تاریخ انتشار

2020

نویسنده

ناشر

شابک

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