Three Dimensional Shock Wave Turbulent Boundary Layer Interactions At Mach 6
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Three Dimensional Shock Wave Turbulent Boundary Layer Interactions At Mach 6
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Author : C. Herbert Law
language : en
Publisher:
Release Date : 1975
Three Dimensional Shock Wave Turbulent Boundary Layer Interactions At Mach 6 written by C. Herbert Law and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1975 with Aerodynamic heating categories.
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.
Three Dimensional Shock Wave Turbulent Boundary Layer Interactions At Mach 6
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Author : C. Herbert Law
language : en
Publisher:
Release Date : 1975
Three Dimensional Shock Wave Turbulent Boundary Layer Interactions At Mach 6 written by C. Herbert Law and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1975 with categories.
Three Dimensional Shock Wave Turbulent Boundary Layer Interactions Generated By A Sharp Fin At Mach 4
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Author : Doyle D. Knight
language : en
Publisher:
Release Date : 1991
Three Dimensional Shock Wave Turbulent Boundary Layer Interactions Generated By A Sharp Fin At Mach 4 written by Doyle D. Knight and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1991 with categories.
Shock Wave Boundary Layer Interactions
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Author : Holger Babinsky
language : en
Publisher: Cambridge University Press
Release Date : 2011-09-12
Shock Wave Boundary Layer Interactions written by Holger Babinsky and has been published by Cambridge University Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 2011-09-12 with Technology & Engineering categories.
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.
Three Dimensional Shock Wave Turbulent Boundary Layer Interaction For A 20 Degrees Sharp Fin At Mach 3
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Author : B. Shapey
language : en
Publisher:
Release Date : 1987
Three Dimensional Shock Wave Turbulent Boundary Layer Interaction For A 20 Degrees Sharp Fin At Mach 3 written by B. Shapey and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1987 with categories.
Three Dimensional Shock Wave And Turbulent Boundary Layer Interactions
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Author : Seymour M. Bogdonoff
language : en
Publisher:
Release Date : 1985
Three Dimensional Shock Wave And Turbulent Boundary Layer Interactions written by Seymour M. Bogdonoff and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1985 with categories.
An extensive experimental study of three-dimensional shock wave turbulent boundary layer interactions caused by shock generators defined solely by angles has been carried out at Mach 3. Sharp fins, sharp swept fins, swept wedges, and semi-cones have been used to generate a wide range of shock waves. The interaction of these waves with turbulent boundary layers has been investigated by surface flow visualization, mean surface static pressure distributions, flowfield surveys of total pressure and yaw, and several flowfield visualization techniques. Some exploratory high frequency surface pressure measurements have been carried out to evaluate the steadiness of these interactions. Scaling laws for both surface and flowfield features have been derived. Some limited studies were carried out at a Mach number of 2. A flowfield study has shown that the initial part of interactions caused by the same strength and geometrical shock wave generated by different shock generators are all similar. The 'footprints' of the interactions, as shown by surface flow visualization, can be categorized as approximately conical or cylindrical, and the boundaries between these two regions have been defined for both Mach 3 and Mach 2. There are still questions with regards to the detailed flowfield structures and physical mechanisms, but the three-dimensional interactions appeared to be less unsteady than that of two-dimensional separated flows.
Theoretical Investigation Of Three Dimensional Shock Wave Turbulent Boundary Layer Interactions Part 4
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Author :
language : en
Publisher:
Release Date : 1986
Theoretical Investigation Of Three Dimensional Shock Wave Turbulent Boundary Layer Interactions Part 4 written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1986 with categories.
A theoretical model consists of the Reynolds-averaged 3-D compressible Navier-Stokes equations, with turbulence incorporated using the algebraic turbulent eddy viscosity model of Baldwin and Lomax, This year research efforts focused on both 2-D and 3-D turbulent interactions. A theoretical model was examined for a series of separated 2-D compression corner flows at Mach 2 and 3. Calculations were performed for four separate compression corners using 2-D compressible Navier-Stodes conde with MacCormack's hybrid algorithm. Results were compared to earlier computations using the Beam-Warming algorithm, and recent experiment data for turbulent Reynolds stresses. Calculated Reynolds stresses were observed to differ significantly from experimental measurements due to the inability of the turbulence model to incorporate the multiple scale effects of the turbulence structure downstream of reattachment. Computed results using the MacCormack hybrid algorithm were observed to be insensitive to the Courant number. The 3-D turbulence interactions research concentrated on the 3-D sharp fin and on the 3-D swept compression corner. In the former case, the computed flowfield for the 20 deg sharp fin at Mach 3 and a Reynolds number of 930,000 was compared with the calculated results of Horstman (who used the Jones-Launder turbulence model) and experimental data of the Princeton Gas Dynamics Lab. Overall comparison with experiment was very good.
Oblique Shock Wave Turbulent Boundary Layer Interactions In Three Dimensions At Mach 3
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Author : B. Oskam
language : en
Publisher:
Release Date : 1976
Oblique Shock Wave Turbulent Boundary Layer Interactions In Three Dimensions At Mach 3 written by B. Oskam and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1976 with categories.
An experimental study, thoroughly documenting the flow field and surface data resulting from the three-dimensional interaction of a shock wave, a shock generator and a high Reynolds number turbulent boundary layer, is described. Detailed surface static pressure data and heat transfer measurements are presented for 7 shock generator deflection angles ranging from 2 to 14 deg. in 2 deg. increments. The test conditions consist of a free stream Reynolds number per inch of 1.6 million, a near adiabatic wall temperature and ambient stagnation temperature. In addition to the surface data detailed flow field surveys have been conducted of time-averaged variables including flow angularity, pitot pressure, static pressure and total temperature at 2 shock generator deflection angles of 4 and 10 degrees. Detailed discussions of the experimental techniques are given which include a complete set of error estimates of the various types of data. Finally the data are presented in graphical form which may be used to analyse the problem under consideration. (Author).
Theoretical Investigation Of Three Dimensional Shock Wave Turbulent Boundary Layer Interactions
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Author : Doyle D. Knight
language : en
Publisher:
Release Date : 1982
Theoretical Investigation Of Three Dimensional Shock Wave Turbulent Boundary Layer Interactions written by Doyle D. Knight and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1982 with categories.
The focus of the research effort is the understanding of three-dimensional shock wave-turbulent boundary layer interactions. The approach uses the full mean compressible Navier-Stokes equations with turbulence incorporated through the algebraic turbulent eddy viscosity model of Baldwin and Lomax. During the present year of the research effort, the three-dimensional shock boundary layer interaction generated by a 10 deg sharp fin has been computed at Mach 3 for a Reynolds number 280000. These results, together with previous computations of the same configuration at Reynolds number = 930000, are compared with experimental data for pitot pressure and yaw angle. The agreement with the experimental data is good, and the theory accurately predicts the recovery of the boundary layer downstream of the interaction of Reynolds number = 280000. The computed flowfield is employed to analyze the structure of the 3-D interaction through contour plots of flow variables. Also, during the present year, the investigation of the 2-D turbulent supersonic compression corner at Mach 3 was completed. The relaxation modification to the Baldwin-Lomax model was found to yield reasonably accurate predictions of the upstream propagation of the surface for the Reynolds number range investigated. An additional computation at Mach 2 was performed, and the results were in general in agreement with the previous conclusions. (Author).
Theoretical Investigation Of Three Dimensional Shock Wave Turbulent Boundary Layer Interactions Part 2
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Author :
language : en
Publisher:
Release Date : 1983
Theoretical Investigation Of Three Dimensional Shock Wave Turbulent Boundary Layer Interactions Part 2 written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1983 with categories.
The focus of the research effort is the understanding of three-dimensional shock wave-turbulent boundary layer interactions. The approach uses the full mean compressible Navier-Stokes equations with turbulence incorporated through the algebraic turbulent eddy viscosity model of Baldwin and Lomax. During the present year of the research effort, the three-dimensional shock boundary layer interaction generated by a 10 deg sharp fin has been computed at Mach 3 for a Reynolds number 280000. These results, together with previous computations of the same configuration at Reynolds number = 930000, are compared with experimental data for pitot pressure and yaw angle. The agreement with the experimental data is good, and the theory accurately predicts the recovery of the boundary layer downstream of the interaction of Reynolds number = 280000. The computed flowfield is employed to analyze the structure of the 3-D interaction through contour plots of flow variables. Also, during the present year, the investigation of the 2-D turbulent supersonic compression corner at Mach 3 was completed. The relaxation modification to the Baldwin-Lomax model was found to yield reasonably accurate predictions of the upstream propagation of the surface for the Reynolds number range investigated. An additional computation at Mach 2 was performed, and the results were in general in agreement with the previous conclusions. (Author).