Wake-shock Interaction at a Mach Number of 6
Author | : Michael J. Walsh |
Publisher | : |
Total Pages | : 196 |
Release | : 1978 |
Genre | : Compressibility |
ISBN | : |
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Author | : Michael J. Walsh |
Publisher | : |
Total Pages | : 196 |
Release | : 1978 |
Genre | : Compressibility |
ISBN | : |
Author | : Michael J. Walsh |
Publisher | : |
Total Pages | : 196 |
Release | : 1978 |
Genre | : Compressibility |
ISBN | : |
Maesuremenas of mean pitot pressure, static pressure, and total temperatire have been made in the two dimensional turbulent mixing regio of a wake downstream of an interaction with a shock-expansion wave sistem. The results indicated that (1) the shock increased the mixing and (2) the expasion field that followed the Shock decreased the turbulent mixing. The overall effect of the shock-expansion wave interaction was dependent on the orientation of the expansion wave with respect to the intersecting shock wave. These dadta could be used to valided nonequilibrium turbulence modeling and numerical solution of the time-averaged Navier-Stokes equations.
Author | : |
Publisher | : |
Total Pages | : 212 |
Release | : 1978 |
Genre | : Science |
ISBN | : |
Author | : C. Herbert Law |
Publisher | : |
Total Pages | : 52 |
Release | : 1975 |
Genre | : Aerodynamic heating |
ISBN | : |
Experimental results of an investigation of the three-dimensional interaction between a skewed shock wave and a turbulent boundary layer are presented. Surface pressure and heat transfer distributions and oil flow photographs were obtained at a freestream Mach number of 5.85 and two Reynolds numbers of ten and twenty million per foot. The model configuration consisted of a shock generator mounted perpendicularly to a flat plate. The shock generator leading edge was sharp and nonswept and intersected the flat plate surface about 8.5 inches downstream of the flat plate leading edge. The shock generator surface was 7.55 inches long and 3 inches high and its angle to the freestream flow was adjusted from 4 to 20 degrees. The generated shock waves were of sufficient strength to produce turbulent boundary layer separation on the flat plate surface.
Author | : |
Publisher | : |
Total Pages | : 994 |
Release | : |
Genre | : Aeronautics |
ISBN | : |
Author | : Konstantinos Kontis |
Publisher | : Springer Science & Business Media |
Total Pages | : 1122 |
Release | : 2012-03-22 |
Genre | : Science |
ISBN | : 3642256856 |
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 | : C. Herbert Law |
Publisher | : |
Total Pages | : 40 |
Release | : 1975 |
Genre | : |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 1230 |
Release | : 1966 |
Genre | : Aeronautics |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 410 |
Release | : 1987 |
Genre | : Aeronautics |
ISBN | : |
Author | : Holger Babinsky |
Publisher | : Cambridge University Press |
Total Pages | : 481 |
Release | : 2011-09-12 |
Genre | : Technology & Engineering |
ISBN | : 1139498649 |
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.