Three Dimensional Shock Wave Turbulent Boundary Layer Interactions Generated By A Sharp Fin At Mach 4
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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.
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.
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.
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).
Experimental Study Of Three Dimensional Shock Wave Turbulent Boundary Layer Interaction Scaling Of Sharp And Blunt Fin Induced Flowfields
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Author : David S. Dolling
language : en
Publisher:
Release Date : 1980
Experimental Study Of Three Dimensional Shock Wave Turbulent Boundary Layer Interaction Scaling Of Sharp And Blunt Fin Induced Flowfields written by David S. Dolling and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1980 with categories.
An experimental study of three-dimensional (3-D) shock wave turbulent boundary layer interaction has been carried out. Interactions generated by fin models having sharp and hemi-cylindrically blunted leading edges have been studied. Tests have been made using incoming turbulent boundary layer varying in thickness in the ratio of about 4:1. Extensive surface property measurements have been made on the test surface on which the incoming boundary layer developed and on the fin itself. All of these tests were carried out at a nominal freestream Mach number of 3, a freestream unit Reynolds number of about 63 million per meter, and under approximately adiabatic wall conditions. The emphasis in the study reported on in this paper was on two main areas. First, to determine the key geometric and/or flow parameters controlling the overall scaling and characteristics of both blunt and sharp fin-induced interactions. Second, to identify the conditions under which both blunt and sharp fins induced interactions have the same local scale and characteristics. (Author).
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.
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.
Intersecting Shock Wave Turbulent Boundary Layer Interactions At Mach 8 3
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-07-08
Intersecting Shock Wave Turbulent Boundary Layer Interactions At Mach 8 3 written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-07-08 with categories.
Experimental data for two three-dimensional intersecting shock-wave/turbulent boundary-layer interaction flows at Mach 8.3 are presented. The test bodies, composed of two sharp fins fastened to a flat-plate test bed, were designed to generate flows with varying degrees of pressure gradient, boundary-layer separation, and turning angle. The data include surface pressure and heat transfer distributions as well as mean flow-field surveys both in the undisturbed and interaction regimes. The data are presented in a convenient form to be used to validate existing or future computational models of these hypersonic flows. The data are also on a 3.5-inch diskette included and are available through E-mail. Kussoy, M. I. and Horstman, K. C. Ames Research Center...
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.
Turbulent Shear Layer Shock Wave Interactions
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Author : J. Delery
language : en
Publisher: Springer Science & Business Media
Release Date : 2013-03-08
Turbulent Shear Layer Shock Wave Interactions written by J. Delery and has been published by Springer Science & Business Media this book supported file pdf, txt, epub, kindle and other format this book has been release on 2013-03-08 with Science categories.
It was on a proposal of the late Professor Maurice Roy, member of the French Academy of Sciences, that in 1982, the General Assembly of the International Union of Theoretical and Applied Mechanics decided to sponsor a symposium on Turbulent Shear-Layer/Shock-Wave Interactions. This sympo sium might be arranged in Paris -or in its immediate vicinity-during the year 1985. Upon request of Professor Robert Legendre, member of the French Academy of Sciences, the organization of the symposium might be provided by the Office National d'Etudes et de Recherches Aerospatiales (ONERA). The request was very favorably received by Monsieur l'Ingenieur General Andre Auriol, then General Director of ONERA. The subject of interactions between shock-waves and turbulent dissipative layers is of considerable importance for many practical devices and has a wide range of engineering applications. Such phenomena occur almost inevitably in any transonic or supersonic flow and the subject has given rise to an important research effort since the advent of high speed fluid mechanics, more than forty years ago. However, with the coming of age of modern computers and the development of new sophisticated measurement techniques, considerable progress has been made in the field over the past fifteen years. The aim of the symposium was to provide an updated status of the research effort devoted to shear layer/shock-wave interactions and to present the most significant results obtained recently.