Analysis of Transonic Normal Shock-Boundary Layer Interaction and Comparisons with Experiment PDF Download
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Author: G. R. Inger
Publisher:
ISBN:
Category :
Languages : en
Pages : 97
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Book Description
Recent progress in the development and application of an analytical theory for non-separating transonic interactions is described. The theory is an approximate multi-layered model leading to a mixed transonic rotational small disturbance flow boundary value problem solved by Fourier transformation methods. Among the results discussed are: (a) a parametric study of Reynolds number effects yielding universal incipient separation curves for weak normal shock interactions; (b) upstream influence and boundary layer thickening; (c) lateral pressure gradient effects and post-shock expansion regions; (d) detailed comparisons with pressure distribution data from both channel flow experiments and supercritical wing test data. (Author).
Author: G. R. Inger
Publisher:
ISBN:
Category :
Languages : en
Pages : 97
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Book Description
Recent progress in the development and application of an analytical theory for non-separating transonic interactions is described. The theory is an approximate multi-layered model leading to a mixed transonic rotational small disturbance flow boundary value problem solved by Fourier transformation methods. Among the results discussed are: (a) a parametric study of Reynolds number effects yielding universal incipient separation curves for weak normal shock interactions; (b) upstream influence and boundary layer thickening; (c) lateral pressure gradient effects and post-shock expansion regions; (d) detailed comparisons with pressure distribution data from both channel flow experiments and supercritical wing test data. (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: Deepak Om
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 358
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Book Description
Author: G. R. Inger
Publisher:
ISBN:
Category :
Languages : en
Pages : 8
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Book Description
Transonic normal shock - turbulent boundary layer interactions can significantly influence not only the local viscous flow but also the downstream behavior of the boundary layer on aerodynamic bodies. It is therefore important that fundamentally-based analytical tools be developed for describing and scaling these interaction effects. This paper examines recent progress toward this goal, with emphasis on two aspects. (1) A basic non-asymptotic triple-deck theory of non-separating two-dimensional interactions that is applicable over a wide range of practical Reynolds numbers and boundary layer profile shapes. (2) Its applicable as a local 'interactive module' in the global transonic flow field analysis of wings, including detailed comparisons with experimental data. Also discussed is the adaptability of this theory to treat interactions involving non-adiabatic wall conditions, including the prediction of incipient separation.
Author: Thomas Charles Adamson
Publisher:
ISBN:
Category : Shock waves
Languages : en
Pages : 152
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Book Description
Author: Sylvester Lung-Yee Zee
Publisher:
ISBN:
Category :
Languages : en
Pages : 282
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 144
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Book Description
Author: D. V. Roscoe
Publisher:
ISBN:
Category :
Languages : en
Pages : 89
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Book Description
The present report discusses the development of a time-dependent Navier-Stokes code for use in predicting transonic shock-wave boundary layer interaction. In addition, various test cases which have been performed are discussed. The algorithm used to solve the equations is based upon the consistently split linearized block implicit method of Briley and McDonald (15, 16). The philosophy and use of a solution adaptive mesh is also described. The test cases studied in this report are: normal shock wave boundary layer interaction in a constant area circular pipe, steady transonic flow over an axisymmetric bump, unsteady flow over an axisymmetric bump, supersonic flow over an axisymmetric compression corner and oblique shock wave impingement on a flat plate boundary layer. (Author).
Author: Reynald Bur
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: George R. Inger
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Book Description
A detailed analysis is made of weak normal shock-turbulent boundary layer interactions on longitudinally-curved surfaces for the case of non-separating steady 2-D flow. It is shown that the interactive viscous displacement effect on the local outer inviscid transonic flow eliminates the well-known singularity pertaining to a curved wall. The inner interaction solution within the boundary layer reveals that curvature moderately influences the interaction through the turbulent eddy viscosity. A non-asymptotic triple-deck solution valid over a wide range of practical Reynolds numbers is given which incorporates this effect, and example numerical results are presented and verified by comparison with experimental data. Small amounts of curvature are found to moderately spread out and thicken the interaction zone while also delaying slightly the onset of any incipient separation that occurs under the shock. (Author).
