Analytical studies of separated vortex flow on highly swept wings PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Analytical studies of separated vortex flow on highly swept wings PDF full book. Access full book title Analytical studies of separated vortex flow on highly swept wings by John M. Kuhlman. Download full books in PDF and EPUB format.
Author: John M. Kuhlman
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 72
Get Book Here
Book Description
Author: John M. Kuhlman
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 72
Get Book Here
Book Description
Author: John M. Kuhlman
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 58
Get Book Here
Book Description
Author: Xing Z. Huang
Publisher: Springer Verlag
ISBN: 9781402093326
Category : Science
Languages : en
Pages : 516
Get Book Here
Book Description
The book discusses the behavior of vortices over sharp and highly swept wing configurations used for current and future military aircraft. Special attention is paid to the effects of critical flow phenomenon such as vortex breakdown occuring at high angles of attack or high angular rates. The wind tunnel experiments conducted on delta-wing configurations in wind tunnels in Canada, Europe, Russia and the United States are given in eight chapters. The experiments provide an extended data base that gives insight into the effects of the angle of attack, angular rate, Reynolds number and Mach number on the behavior of vortices over several slender delta wings in stationary and instationary flights. A critical assessment is given in a separated chapter of the available experimental data bases and out of these data, one and the same data set is selected for the validation and verification of analytical and numerical solutions.Comprehansive computational results are given in another ten chapters. Steady-state and time-accurate solutions for the steady and unsteady flow over the selected delta-wing configuration are discussed. These solutions are generated using structured and unstructured grid methods.The analytical solutions for the flow over a delta wing are discussed and compared with experimental data in three more chapters.In the final chapter a validation and verification of the analytical and CFD solutions is given.
Author: Kaufman Louis G. (II)
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 60
Get Book Here
Book Description
Shock-induced flow-separation ahead of trailing edge controls on swept wings is investigated with emphasis on the effects of boundary layer transition on the location and shape of the separation line. Experimental results were obtained by using forward facing steps mounted on swept-leading-edge flat-plate wing models in the ARL Mach 6 Tunnel for model running length Reynolds numbers varying from 0.9 to 33 million. The data support qualitatively a proposed, strip-type method for estimating, the extent and shape of the three dimensional region of separated flow ahead of controls on swept wings. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 984
Get Book Here
Book Description
Author: National Aeronautics and Space Administration
Publisher:
ISBN: 9781726147910
Category :
Languages : en
Pages : 80
Get Book Here
Book Description
A discrete-vortex method is developed to investigate the wing rock problem associated with highly swept wings. The method uses two logarithmic vortices placed above the wing to represent the vortex flow field and uses boundary conditions based on conical flow, vortex rate of change of momentum, and other considerations to position the vortices and determine their strengths. A relationship based on the time analogy and conical-flow assumptions is used to determine the hysteretic positions of the vortices during roll oscillations. Static and dynamic vortex positions and wing rock amplitudes and frequencies calculated by using the method are generally in good agreement with available experimental data. The results verify that wing rock is caused by hysteretic deflections of the vortices and indicate that the stabilizing moments that limit wing rock amplitudes are the result of the one primary vortex moving outboard of the wing where it has little influence on the wing.Gainer, Thomas G.Langley Research CenterWING ROCK; VORTICES; FLOW DISTRIBUTION; DYNAMIC STABILITY; DELTA WINGS; STABILIZATION; SWEPT WINGS; HYSTERESIS; FLOW VELOCITY; DEFLECTION; CONICAL FLOW; BOUNDARY CONDITIONS; ANALOGIES...
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781723937125
Category :
Languages : en
Pages : 80
Get Book Here
Book Description
A discrete-vortex method is developed to investigate the wing rock problem associated with highly swept wings. The method uses two logarithmic vortices placed above the wing to represent the vortex flow field and uses boundary conditions based on conical flow, vortex rate of change of momentum, and other considerations to position the vortices and determine their strengths. A relationship based on the time analogy and conical-flow assumptions is used to determine the hysteretic positions of the vortices during roll oscillations. Static and dynamic vortex positions and wing rock amplitudes and frequencies calculated by using the method are generally in good agreement with available experimental data. The results verify that wing rock is caused by hysteretic deflections of the vortices and indicate that the stabilizing moments that limit wing rock amplitudes are the result of the one primary vortex moving outboard of the wing where it has little influence on the wing.Gainer, Thomas G.Langley Research CenterWING ROCK; VORTICES; FLOW DISTRIBUTION; DYNAMIC STABILITY; DELTA WINGS; STABILIZATION; SWEPT WINGS; HYSTERESIS; FLOW VELOCITY; DEFLECTION; CONICAL FLOW; BOUNDARY CONDITIONS; ANALOGIES
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1362
Get Book Here
Book Description
Author: Paul K. Chang
Publisher: Elsevier
ISBN: 1483181286
Category : Technology & Engineering
Languages : en
Pages : 800
Get Book Here
Book Description
Interdisciplinary and Advanced Topics in Science and Engineering, Volume 3: Separation of Flow presents the problem of the separation of fluid flow. This book provides information covering the fields of basic physical processes, analyses, and experiments concerning flow separation. Organized into 12 chapters, this volume begins with an overview of the flow separation on the body surface as discusses in various classical examples. This text then examines the analytical and experimental results of the laminar boundary layer of steady, two-dimensional flows in the subsonic speed range. Other chapters consider the study of flow separation on the two-dimensional body, flow separation on three-dimensional body shape and particularly on bodies of revolution. This book discusses as well the analytical solutions of the unsteady flow separation. The final chapter deals with the purpose of separation flow control to raise efficiency or to enhance the performance of vehicles and fluid machineries involving various engineering applications. This book is a valuable resource for engineers.
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 992
Get Book Here
Book Description
