Spatial And Temporal Features Of A Separated Flow Field At A Convex Wall Induced By Normal Shock Wave Turbulent Boundary Layer Interaction PDF Download
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Author | : P. Doerffer |
Publisher | : |
Total Pages | : |
Release | : 1990 |
Genre | : |
ISBN | : |
Download Spatial and Temporal Features of a Separated Flow Field at a Convex Wall Induced by Normal Shock Wave Turbulent Boundary Layer Interaction Book in PDF, ePub and Kindle
Author | : Klaus Gersten |
Publisher | : Springer Science & Business Media |
Total Pages | : 305 |
Release | : 2013-06-29 |
Genre | : Science |
ISBN | : 3663139867 |
Download Physics of Separated Flows — Numerical, Experimental, and Theoretical Aspects Book in PDF, ePub and Kindle
This volume contains 37 contributions in which the research work is summarized which has been carried out between 1984 and 1990 in the Priority Research Program "Physik abgeloster Stromungen" of the Deutsche Forschungsgemeinschaft (DFG, German Research Society). The aim of the Priority Research Program was the inten sive research of the whole range of phenomena associated with separated flows. Physi cal models as well as prediction methods had to be developed based on detailed experi mental investigations. It was in accordance with the main concept of the research program that scientists working on problems of separated flows in different technical areas of application participated in this program. The following fields have been represented in the program: aerodynamics of wings and bodies, aerodynamics of auto mobiles, turbomachinery, ship hydrodynamics, hydraulics, internal flows, heat exchan gers, bio-fluid-dynamics, aerodynamics of buildings and structures. In order to concentrate on problems common in all those areas the emphasis of the program was on basic research dealing with generic geometric configurations showing the fundamental physical phenomena of separated flows. The engagement and enthusiasm of all participating scientists are highly appreciated. The program was organized such that all researchers met once a year to report on the progress of their work. Special thanks ought to go to Prof. E. A. Muller (Gottingen), Prof. H. Oertel jun. (Braunschweig), Dr. W. Schmidt (Dornier), Dr. H. -W. Stock (Dornier) and Dr. B. Wagner (Dornier), who had the functions of referees on those annual meetings.
Author | : |
Publisher | : |
Total Pages | : 390 |
Release | : 1990 |
Genre | : Fluid dynamics |
ISBN | : |
Download AIAA 90-1440 - AIAA 90-1470 Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 1068 |
Release | : 1990 |
Genre | : Aeronautics |
ISBN | : |
Download International Aerospace Abstracts Book in PDF, ePub and Kindle
Author | : D. O. Davis |
Publisher | : |
Total Pages | : 24 |
Release | : 1992 |
Genre | : Turbulent boundary layer |
ISBN | : |
Download Surface and Flow Field Measurements in a Symmetric Crossing Shock Wave/turbulent Boundary-layer Interaction Book in PDF, ePub and Kindle
Author | : G. R. Inger |
Publisher | : |
Total Pages | : 8 |
Release | : 1981 |
Genre | : |
ISBN | : |
Download Some Fundamental Aspects of Shock Wave - Turbulent Boundary Interactions in Transonic Flow Book in PDF, ePub and Kindle
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 | : |
Publisher | : |
Total Pages | : 1346 |
Release | : 1985 |
Genre | : Aeronautics |
ISBN | : |
Download Scientific and Technical Aerospace Reports Book in PDF, ePub and Kindle
Author | : Chen-Chih Sun |
Publisher | : |
Total Pages | : 116 |
Release | : 1976 |
Genre | : Fluid dynamics |
ISBN | : |
Download Flowfield Analysis for Successive Oblique Shock Wave-turbulent Boundary Layer Interactions Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 338 |
Release | : 1987 |
Genre | : Mechanics, Applied |
ISBN | : |
Download Applied Mechanics Reviews Book in PDF, ePub and Kindle
Author | : W. H. Schofield |
Publisher | : |
Total Pages | : 12 |
Release | : 1983 |
Genre | : Shock waves |
ISBN | : 9780642078964 |
Download Interaction of a Turbulent Boundary Layer with a Normal Shock Wave Followed by an Adverse Pressure Gradient Book in PDF, ePub and Kindle
An experimental study was made of the development of a turbulent boundary layer after an interaction with a normal shock wave (strong enough to cause a local separation) in a strong adverse pressure gradient. This type of flow, which occurs in air breathing engine components (e.g. supersonic intakes, transonic compressor stages and supersonic diffusers), is poorly understood and cannot be satisfactorily predicted. The measurements, made in a closed duct, extended well downstream of the shock wave interaction. Detailed results for the flow are presented and used to support two major conclusions. It is shown that the post shock adverse pressure gradient has a large effect on boundary layer development through the interaction and downstream of it. Consequently existing results for interactions without a post shock pressure gradient should not be used as a model for practical flows which typically have strong pressure gradients applied downstream of the shock wave. The second conclusions was that the shock wave in a rectangular duct produced a pronounced stabilising effect on the downstream flow. Surface flow visualization suggests that this stabilization is achieved by streamwise vortices shed into the flow from the separated region formed by the shock wave. Implications of this result to nominally two-dimensional flow situations and to flows with weak interactions without local separations are discussed.