Author: P. H. Oosthuizen
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 41

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Book Description
A theoretical study of the effects of the wall boundary layer on the supersonic flow around a sharp convex corner is presented. Fundamentally different methods of analysis are adopted for laminar and for turbulent boundary layers. In the case of interactions involving laminar boundary layers, an analysis based on the use of classical boundary layer theory is used. Results of numerical calculations carried out using this analysis to predict the effects of the major governing parameters are presented. In all cases, a considerable upstream and downstream influence is predicted. A simplified form of this analysis, closely related to that of Curle, is also presented, this analysis leading to a simple set of explicit equations describing the flow quantities in the interaction region. Comparison of the simplified analysis with results obtained from the full analysis indicated, as is to be expected, that the simplified analysis will only give acceptable results for small expansion angles and moderate Mach numbers. In the case of turbulent boundary layer interactions, an analysis based on the assumption that there is no upstream influence and that the major portion of the expansion occurs in an effectively inviscid manner is adopted, the flow properties being calculated by the method of rotational characteristics. (Author).

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: University of Toronto. Institute for Aerospace Studies
Publisher:
ISBN:
Category :
Languages : en
Pages : 90

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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 40

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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 48

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Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 828

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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704

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Author: Philip A. Sullivan
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 15

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Book Description
A simple method of calculating the extent of the interaction of a corner expansion wave with a hypersonic boundary layer is presented. Arguments are presented to suggest that for small turning angles the principal feature of the flow is the interaction of the boundary layer and the expansion wave downstream of the corner. The net result is a large increase in the thickness of the boundary layer, and a greatly extended region of pressure decay. Numerical results based on the 'cold wall' or local similarity approximation are given. (Author).

Author: A. K. Lo
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 48

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Book Description
The thesis describes a study of the application of Dorodnitsyn's method of integral relations and some related techniques belonging to the method of weighted residuals to hypersonic laminar boundary layer problems. Numerical Galerkin-Dorodnitsyn single strip solutions to the viscous-inviscid equations are presented for small turning angles, corner radii comparable to the boundary layer thickness and distances downstream to the point where transverse pressure gradients become negligible. The results show small upstream influence, extended downstream boundary layer-expansion wave interaction, significant pressure differences across the boundary layer, and weak overexpansion of the pressure at the edge of the layer. They also show a peak in heat transfer and skin friction at the corner, and suggest that the extent of the interaction would not be detected by measuring wall pressure. Comparisons of the methods are also made for boundary layer obeying the classical Prandtl equations. (Author).

Author: A. K. Lo
Publisher: National Library of Canada
ISBN:
Category :
Languages : en
Pages :

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