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Author: G. Smeets
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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Book Description
Author: G. Smeets
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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Book Description
Author: Ernst Rudolf Georg Eckert
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 118
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Book Description
Author: Tuncer Cebeci
Publisher: Elsevier
ISBN: 0323151051
Category : Technology & Engineering
Languages : en
Pages : 423
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Book Description
Analysis of Turbulent Boundary Layers focuses on turbulent flows meeting the requirements for the boundary-layer or thin-shear-layer approximations. Its approach is devising relatively fundamental, and often subtle, empirical engineering correlations, which are then introduced into various forms of describing equations for final solution. After introducing the topic on turbulence, the book examines the conservation equations for compressible turbulent flows, boundary-layer equations, and general behavior of turbulent boundary layers. The latter chapters describe the CS method for calculating two-dimensional and axisymmetric laminar and turbulent boundary layers. This book will be useful to readers who have advanced knowledge in fluid mechanics, especially to engineers who study the important problems of design.
Author: Larry L. Lynes
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 72
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Book Description
The method of integral relations was successfully applied to compressible nonadiabatic turbulent boundary layers on a flat plate. The theory is designed to accept any desired eddy-viscosity model. A particular eddy-viscosity model was incorporated into the method, and the equations were programmed for application to a flat plate with no pressure gradient. The variations of the skin-friction coefficient with Reynolds number, Mach number, and temperature ratio were calculated using this program, and the results are in good accord with similar results calculated by the Spalding-Chi method and the Rubesin T' method. An analysis was made to predict to what extent turbulent separation of the free-interaction type can be inhibited by means of surface cooling. It was observed experimentally that free-interaction is applicable to separated turbulent boundary layers up to the separation point or beyond. The free-interaction model used in the analysis is based on adding the boundary-layer displacement thickness to the actual body dimensions in calculating the induced pressures. The critical temperature ratios calculated on this basis are generally greater than adiabatic wall temperature except in the supersonic range up to a Mach number approaching 3, where moderate cooling is required to inhibit separation.
Author: Paul F. Brinich
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 36
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Book Description
An analysis of time-mean-turbulent boundary layer velocity profiles measured in a rapidly accelerating flow suggests that the outer region of the velocity profiles consists of essentially inviscid, rotational flow. The extent of this inviscid outer region was observed in some cases to exceed 90 percent of what is ordinarily thought of as the turbulent boundary layer thickness. On the other hand, the inner frictional region of these velocity profiles appears to have turbulent characteristics similar to those of more conventional turbulent boundary layers. Hence, the outer edge boundary condition for this inner region is more properly the external rotational flow region than the free stream.
Author: Michael E. Tauber
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 44
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Book Description
Author: Michael L. Finson
Publisher:
ISBN:
Category :
Languages : en
Pages : 45
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Book Description
Attempts at developing an improved engineering method for predicting separated supersonic turbulent flows are reported. The approach is based on the use of an inverse boundary layer method, coupled with a five-equation Reynolds stress turbulence model, comparisons of results of the turbulence model with measurements on attached boundary layers in adverse boundary layers showed that the model predicts too large an increase in the turbulent Reynolds stress. Most of the existing inverse boundary layer methods could not be readily applied to the present problem. A second approach was adopted, but proved to be not very 'robust'. Attempts to simulate separated flows failed to yield a proper separation zone, apparently due to excessive build-up of the Reynolds stress. Finally, it is noted that reliable algorithms for matching the boundary layer solution in the outer inviscid flow need to be developed.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 52
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Book Description
Author: Holger Babinsky
Publisher: Cambridge University Press
ISBN: 1139498649
Category : Technology & Engineering
Languages : en
Pages : 481
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Book Description
Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines. SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.
Author: Constantino Economos
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 132
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Book Description
This report investigates the behavior of high speed turbulent boundary layer with heat transfer and streamwise pressure gradient.
