A Study of the Interaction Between a Glancing Shock Wave and a Turbulent Boundary Layer PDF Download
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Author: H. Kubota
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: H. Kubota
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: A. Hussain
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Author: Aeronautical Research Council (Great Britain)
Publisher:
ISBN:
Category : Glancing interaction
Languages : en
Pages : 8
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Author:
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ISBN:
Category :
Languages : en
Pages : 8
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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: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722499792
Category :
Languages : en
Pages : 98
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A preliminary experimental investigation was conducted to study two crossing, glancing shock waves of equal strengths, interacting with the boundary-layer developed on a supersonic wind tunnel wall. This study was performed at several Mach numbers between 2.5 and 4.0. The shock waves were created by fins (shock generators), spanning the tunnel test section, that were set at angles varying from 4 to 12 degrees. The data acquired are wall static pressure measurements, and qualitative information in the form of oil flow and schlieren visualizations. The principle aim is two-fold. First, a fundamental understanding of the physics underlying this flow phenomena is desired. Also, a comprehensive data set is needed for computational fluid dynamic code validation. Results indicate that for small shock generator angles, the boundary-layer remains attached throughout the flow field. However, with increasing shock strengths (increasing generator angles), boundary layer separation does occur and becomes progressively more severe as the generator angles are increased further. The location of the separation, which starts well downstream of the shock crossing point, moves upstream as shock strengths are increased. At the highest generator angles, the separation appears to begin coincident with the generator leading edges and engulfs most of the area between the generators. This phenomena occurs very near the 'unstart' limit for the generators. The wall pressures at the lower generator angles are nominally consistent with the flow geometries (i.e. shock patterns) although significantly affected by the boundary-layer upstream influence. As separation occurs, the wall pressures exhibit a gradient that is mainly axial in direction in the vicinity of the separation. At the limiting conditions the wall pressure gradients are primarily in the axial direction throughout. Hingst, Warren R. and Williams, Kevin E. Glenn Research Center...
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 100
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Author: James Wilbert Cutbirth
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 88
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Author: I. E. Vas
Publisher:
ISBN:
Category :
Languages : en
Pages : 8
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Author: Earl C. Watson
Publisher:
ISBN:
Category : Laminar boundary layer
Languages : en
Pages : 140
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Book Description
Laminar and turbulent boundary layer interactions with externally generated shock waves.
