Separated And Vortical Flow In Aircraft Wing Aerodynamics Download Ebook PDF Epub Online

Author : Ernst Heinrich Hirschel
Arthur Rizzi
Publisher : Springer Nature
Release : 2020-11-05
Page : 456
Category : Technology & Engineering
ISBN 13 : 366261328X
Description :


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.


Author : Ernst Heinrich Hirschel
Arthur Rizzi
Publisher : Springer
Release : 2020-11-22
Page : 459
Category : Technology & Engineering
ISBN 13 : 9783662613269
Description :


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.


Author :
Publisher :
Release : 1983
Page : 34
Category :
ISBN 13 :
Description :



Author : Wei Shyy
Hikaru Aono
Publisher : Cambridge University Press
Release : 2013-08-19
Page :
Category : Technology & Engineering
ISBN 13 : 1107067987
Description :


This is an ideal book for graduate students and researchers interested in the aerodynamics, structural dynamics and flight dynamics of small birds, bats and insects, as well as of micro air vehicles (MAVs), which present some of the richest problems intersecting science and engineering. The agility and spectacular flight performance of natural flyers, thanks to their flexible, deformable wing structures, as well as to outstanding wing, tail and body coordination, is particularly significant. To design and build MAVs with performance comparable to natural flyers, it is essential that natural flyers' combined flexible structural dynamics and aerodynamics are adequately understood. The primary focus of this book is to address the recent developments in flapping wing aerodynamics. This book extends the work presented in Aerodynamics of Low Reynolds Number Flyers (Shyy et al. 2008).


Author :
Publisher :
Release : 1992
Page :
Category : Aeronautics
ISBN 13 :
Description :



Author : Edward Lewis Houghton
Publisher :
Release : 1978
Page : 458
Category :
ISBN 13 :
Description :



Author : Andreas Dillmann
Gerd Heller
Publisher : Springer Nature
Release : 2019-09-26
Page : 867
Category : Technology & Engineering
ISBN 13 : 3030252531
Description :


This book gathers contributions to the 21st biannual symposium of the German Aerospace Aerodynamics Association (STAB) and the German Society for Aeronautics and Astronautics (DGLR). The individual chapters reflect ongoing research conducted by the STAB members in the field of numerical and experimental fluid mechanics and aerodynamics, mainly for (but not limited to) aerospace applications, and cover both nationally and EC-funded projects. Special emphasis is given to collaborative research projects conducted by German scientists and engineers from universities, research-establishments and industries. By addressing a number of cutting-edge applications, together with the relevant physical and mathematics fundamentals, the book provides readers with a comprehensive overview of the current research work in the field. The book’s primary emphasis is on aerodynamic research in aeronautics and astronautics, and in ground transportation and energy as well.


Author : Mohamed Gad-el-Hak
Publisher : Springer Science & Business Media
Release : 2013-03-08
Page : 532
Category : Science
ISBN 13 : 3642838316
Description :


Dynamical systems theory and flow control are two research areas of great current interest. These and other special situations are among the topics covered in this volume. Each article emphasizes the use of experiments to achieve better physical understanding of a particular class of flow problems. The topics covered were chosen because of their importance to the field, recent appeal, and potential for future development. The articles are comprehensive and coverage is pedagogical with a bias towards recent developments.


Author : Josef Rom
Publisher : Springer Science & Business Media
Release : 2012-12-06
Page : 399
Category : Science
ISBN 13 : 1461228247
Description :


The aerodynamics of aircraft at high angles of attack is a subject which is being pursued diligently, because the modern agile fighter aircraft and many of the current generation of missiles must perform well at very high incidence, near and beyond stall. However, a comprehensive presentation of the methods and results applicable to the studies of the complex aerodynamics at high angle of attack has not been covered in monographs or textbooks. This book is not the usual textbook in that it goes beyond just presenting the basic theoretical and experimental know-how, since it contains reference material to practical calculation methods and technical and experimental results which can be useful to the practicing aerospace engineers and scientists. It can certainly be used as a text and reference book for graduate courses on subjects related to high angles of attack aerodynamics and for topics related to three-dimensional separation in viscous flow courses. In addition, the book is addressed to the aerodynamicist interested in a comprehensive reference to methods of analysis and computations of high angle of attack flow phenomena and is written for the aerospace scientist and engineer who is familiar with the basic concepts of viscous and inviscid flows and with computational methods used in fluid dynamics.


Author : Ning Qin
Jacques Periaux
Publisher : Springer Nature
Release : 2019-10-17
Page : 341
Category : Technology & Engineering
ISBN 13 : 3030296881
Description :


This book presents the results of a European-Chinese collaborative research project, Manipulation of Reynolds Stress for Separation Control and Drag Reduction (MARS), including an analysis and discussion of the effects of a number of active flow control devices on the discrete dynamic components of the turbulent shear layers and Reynolds stress. From an application point of view, it provides a positive and necessary step to control individual structures that are larger in scale and lower in frequency compared to the richness of the temporal and spatial scales in turbulent separated flows.


Author : Jie-Zhi Wu
Hui-Yang Ma
Publisher : Springer
Release : 2015-06-23
Page : 446
Category : Technology & Engineering
ISBN 13 : 3662470616
Description :


This book is a comprehensive and intensive book for graduate students in fluid dynamics as well as scientists, engineers and applied mathematicians. Offering a systematic introduction to the physical theory of vortical flows at graduate level, it considers the theory of vortical flows as a branch of fluid dynamics focusing on shearing process in fluid motion, measured by vorticity. It studies vortical flows according to their natural evolution stages,from being generated to dissipated. As preparation, the first three chapters of the book provide background knowledge for entering vortical flows. The rest of the book deals with vortices and vortical flows, following their natural evolution stages. Of various vortices the primary form is layer-like vortices or shear layers, and secondary but stronger form is axial vortices mainly formed by the rolling up of shear layers. Problems are given at the end of each chapter and Appendix, some for helping understanding the basic theories, and some involving specific applications; but the emphasis of both is always on physical thinking.


Author : Richard M. Wood
Publisher :
Release : 2003
Page : 100
Category : Aerodynamics, Supersonic
ISBN 13 :
Description :



Author : Alvin H. Sacks
Jack Norman Nielsen
Publisher :
Release : 1961
Page : 126
Category : Aerodynamics
ISBN 13 :
Description :


A mathematical theory is developed for the lowspeed aerodynamics of rectangular wings with side-edge separation. The assumed vortex system consists of a lifting line with its associated trailing sheet (lying in the plane of t e wing) and a separated vortex sheet from each side edge with an associated bound vortex system in the wing. The Kutta condition is satisfied along the side edges, and the boundary condition of no flow through the wing is satisfied along a selected control line for all spanwise points by means of Fourier analysis. The resulting theory includes the classical lifting-line theory of Prandtl and provides a means of calculating the downwash anywhere in the plane of the lifting line. Calculations were made of the normal force, span loading, and center e for a rectangular wing of aspect ratio two, and comparisons with experiment are presented. The analysis is extended to wings with sweptback leading edges (and straight trailing edges) by representing the actual wing as a system of elementary rectangular wings of varying aspect ratio. For extremely large sweep angles, a method is presented for calculating the normal force on general slender configurations with leading-edge separation using the cross-flow drag concept. (Authof pressure for a rectangular wing of aspect ratio two, and comparisons with experiment are presented. The analysis is extended to wings with sweptback leading edges (and straight trailing edges) by representing the actual wing as a system of elementary rectangular wings of varying aspect ratio. For extremely large sweep angles, a method is presented for calculating the normal force on general slender configurations with leading-edge separation using the cross-flow drag concept. (Author).


Author :
Publisher :
Release : 1984
Page :
Category : Aeronautics
ISBN 13 :
Description :



Author :
Publisher :
Release : 1973
Page :
Category : Military research
ISBN 13 :
Description :



Author :
Publisher :
Release : 1985
Page : 573
Category :
ISBN 13 :
Description :



Author : ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (France)
Publisher :
Release : 1983
Page : 554
Category :
ISBN 13 :
Description :


Vortical flows are an inevitable feature of almost all flow fields of aeronautical interest. For example, they arise from leading and trailing edges of wings, from bodies at high angles of attack and are always evident in separated flows. They can have major effects on the loading of surfaces with which they interact. They are sometimes stable and well ordered and their effects can then be beneficient and exploitable, but when unstable their effects are generally adverse. To expand the flight envelopes and controllability of modern aircraft we need to improve considerably our understanding of such flows as they are at th root of many important design problems. The Symposium was divided into five sessions with the following topic headings: Fundamental Generation and Structure of Vortical Flows, Interaction of Vortical Flows with Surfaces, Modelling and Computing, Stability and Breakdown of Vortical Flows, Control and Exploitation of Vortical Flows. The papers showed that in all the main areas of interest considerable progress has made in recent years, but much remains to be done. We have a good topological basis for describing separated flows and the associated vortical flow regions: the computation of inviscid models (e.g. panel methods, Euler equation solutions, convected vortex element methods) is developing well; and practical forms of control and exploitation have been sucessfully demonstrated.


Author : Wieslaw Zenon Stepniewski
C. N. Keys
Publisher : Courier Corporation
Release : 1984
Page : 601
Category : Science
ISBN 13 : 9780486646473
Description :


Recent literature related to rotary-wing aerodynamics has increased geometrically; yet, the field has long been without the benefit of a solid, practical basic text. To fill that void in technical data, NASA (National Aeronautics and Space Administration) commissioned the highly respected practicing engineers and authors W. Z. Stepniewski and C. N. Keys to write one. The result: Rotary-Wing Aerodynamics, a clear, concise introduction, highly recommended by U.S. Army experts, that provides students of helicopter and aeronautical engineering with an understanding of the aerodynamic phenomena of the rotor. In addition, it furnishes the tools for quantitative evaluation of both rotor performance and the helicopter as a whole. Now both volumes of the original have been reprinted together in this inexpensive Dover edition. In Volume I: "Basic Theories of Rotor Aerodynamics," the concept of rotary-wing aircraft in general is defined, followed by comparison of the energy effectiveness of helicopters with that of other static-thrust generators in hover, as well as with various air and ground vehicles in forward translation. Volume II: "Performance Prediction of Helicopters" offers practical application of the rotary-wing aerodynamic theories discussed in Volume I, and contains complete and detailed performance calculations for conventional single-rotor, winged, and tandem-rotor helicopters. Graduate students with some background in general aerodynamics, or those engaged in other fields of aeronautical or nonaeronautical engineering, will find this an essential and thoroughly practical reference text on basic rotor dynamics. While the material deals primarily with the conventional helicopter and its typical regimes of flight, Rotary-Wing Aerodynamics also provides a comprehensive insight into other fields of rotary-wing aircraft analysis as well.


Author : Howard F. Savage
Publisher :
Release : 1957
Page : 82
Category : Aerodynamics
ISBN 13 :
Description :


An investigation has been conducted to determine the effects of vertical-tail location and size on the subsonic aerodynamic characteristics of a model having a triangular wing. The wing had an aspect ratio of 3, an NACA 0003.5-63 section in the streamwise direction, and plain, trailing-edge ailerons. The wing was attached to the fuselage in either a mid or high position and an unswept horizontal tail was located on the fuselage center line. Two vertical tails were tested which had areas of 26.7 or 20.3 percent of the wing area. Each vertical tail was equipped with a rudder and had a geometric aspect ratio of 1.5, a taper ratio of 0.16, and 54 degrees of sweepback of the leading edge. Each vertical tail was tested at two different tail lengths. The wind-tunnel tests were conducted at a Reynolds number of 2.5 milMon at Mach numbers from 0.25 to 0.95.


Author : Farhad Ghaffari
Publisher :
Release : 1994
Page : 67
Category : Hornet (Jet fighter plane)
ISBN 13 :
Description :