Flow Structure of Supersonic Flow Past Backward-facing Step with Perpendicular Injector
Author : Akiko Matsuo
Publisher :
Page : pages
File Size : 30,21 MB
Release : 1998
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Author : Akiko Matsuo
Publisher :
Page : pages
File Size : 30,21 MB
Release : 1998
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Author : Konstantinos Kontis
Publisher : Springer Science & Business Media
Page : 860 pages
File Size : 17,18 MB
Release : 2012-03-14
Category : Science
ISBN : 3642256880
The University of Manchester hosted the 28th International Symposium on Shock Waves between 17 and 22 July 2011. The International Symposium on Shock Waves first took place in 1957 in Boston and has since become an internationally acclaimed series of meetings for the wider Shock Wave Community. The ISSW28 focused on the following areas: Blast Waves, Chemically Reacting Flows, Dense Gases and Rarefied Flows, Detonation and Combustion, Diagnostics, Facilities, Flow Visualisation, Hypersonic Flow, Ignition, Impact and Compaction, Multiphase Flow, Nozzle Flow, Numerical Methods, Propulsion, Richtmyer-Meshkov, Shockwave Boundary Layer Interaction, Shock Propagation and Reflection, Shock Vortex Interaction, Shockwave Phenomena and Applications, as well as Medical and Biological Applications. The two Volumes contain the papers presented at the symposium and serve as a reference for the participants of the ISSW 28 and individuals interested in these fields.
Author : Kaveh Taghavi
Publisher :
Page : 240 pages
File Size : 41,66 MB
Release : 1988
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Author : Seong-Ok Choy
Publisher :
Page : 224 pages
File Size : 29,35 MB
Release : 1998
Category : Aerodynamics, Supersonic
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Author : Abdallah Antoun Sfeir
Publisher :
Page : 66 pages
File Size : 11,33 MB
Release : 1966
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Author : Eric Loth
Publisher :
Page : pages
File Size : 15,79 MB
Release : 1990
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Author : S. Y. Yang
Publisher :
Page : pages
File Size : 13,10 MB
Release : 2001
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Author : Odus R. Burggraf
Publisher :
Page : 56 pages
File Size : 11,16 MB
Release : 1970
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The problem of laminar separated flow over a backward-facing step is solved numerically for the limiting case of infinite Reynolds number. The flow model adopted is that deduced by Batchelor for incompressible flow: an inviscid rotational eddy confined within the recirculation portion of the separated shear layer. It is argued that the reattachment process is essentially inviscid in the limit R approaches infinity, and the flow field in the reattachment zone is computed on this basis. The computed results support Chapman's model of the reattachment process as the correct limit case, to second-order accuracy, as the flow angle entering the reattachment zone approaches zero. For the recirculation zone, the boundary-layer equations are simplified by assuming a constant pressure eddy. The Dorodnitsyn transformation is applied and numerical solutions obtained using an implicit finite-difference scheme. The solutions are carried out from station-to-station in the direction of flow over a complete cycle of recirculation. Iteration yields the unique value of the vorticity in the inviscid layer upstream of separation, including the effects of corner expansion and recirculation on the development of the separated shear layer. (Author).
Author :
Publisher :
Page : 638 pages
File Size : 35,56 MB
Release : 1997
Category : Aeronautics
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Author : Harry Allen Berman
Publisher :
Page : 180 pages
File Size : 21,9 MB
Release : 1981
Category : Aerodynamics, Supersonic
ISBN :