Oblique Shock Wave Turbulent Boundary Layer Interactions In Three Dimensions At Mach 3
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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 : 1978
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 1978 with categories.
The second phase of a detailed experimental investigation has been carried out on the interaction between oblique shock waves and turbulent boundary layers in three dimensions. The present work extends the original region of study of the shock wave interaction area towards the streamwise corner between the shock generator and the test wall. The purpose of this report is to present the experimental data in tabulated form. The tabulations include both surface data such as heat transfer and static pressure as well as detailed flow field surveys of pitot pressure, flow angularity, static pressure and total temperature.
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).
An Exploratory Study Of A Three Dimensional Shock Wave Boundary Layer Interaction At Mach 3
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Author : B. Oskam
language : en
Publisher:
Release Date : 1975
An Exploratory Study Of A Three Dimensional Shock Wave Boundary Layer Interaction 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 1975 with categories.
An exploratory experimental investigation has been carried out on the three dimensional flow fields caused by the interaction of oblique shock waves and a planar turbulent boundary layer. The study was performed at a free stream Mach number of 2.95, a Reynolds number per inch of 1.6 million and near adiabatic wall conditions. The interaction was studied on two experimental configurations having different initial boundary layer thicknesses (delta = approx. 0.13 and 0.55 inches). Both surface measurements as well as complete flow field surveys were performed. The main contributions of the present investigation are two experimentally derived flow field models for shock generator angles of 4 deg and 10 deg. Based upon both static pressure and surface flow patterns, as well as heat transfer data, the interaction region can be characterized as quasi-two-dimensional along the shock direction in the region studied. A critical examination of the occurrence of 'ordinary' flow separation and its character, as applied to the present problem, was carried out. It was concluded that McCabe's criterion, as used by the previous investigators, is not a sufficient condition to determine the onset of flow separation.
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.
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 Swept Shock Turbulent Boundary Layer Separations With Control By Air Injection
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Author : D. J. Peake
language : en
Publisher:
Release Date : 1976
Three Dimensional Swept Shock Turbulent Boundary Layer Separations With Control By Air Injection written by D. J. Peake and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1976 with Turbulent boundary layer categories.
Experimentally determined wall pressure distributions, local surface shear stresses and their directions, and detailed turbulent boundary-layer traverses in near zero heat transfer conditions, are presented through skewed shock/boundary-layer interaction regions generated by a wedge standing normal to a test wall. The mainstream Mach numbers were 2 and 4, while the Reynolds number based on the undisturbed test boundary-layer thickness of 0.2-in., growing along the nozzle sidewall of the NAE 5 X 5-in. blowdown wind tunnel, was 200,000. Tangential air injection at a jet exit Mach number of 3 was then introduced into the 3D shock separated Mach 2 boundary layer, to control the separation. The optimum direction of blowing was found to be along a line somewhere between the deflected surface of the wedge and the line of the oblique shock wave.
Numerical Solution To The Glancing Sidewall Oblique Shock Wave Turbulent Boundary Layer Interaction In Three Dimension
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Author : B.H. Anderson
language : en
Publisher:
Release Date : 1983
Numerical Solution To The Glancing Sidewall Oblique Shock Wave Turbulent Boundary Layer Interaction In Three Dimension written by B.H. Anderson 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.
Study Of Three Dimensional Flow Fields Generated By The Interaction Of A Skewed Shock Wave With A Turbulent Boundary Layer
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Author : B. Oskam
language : en
Publisher:
Release Date : 1975
Study Of Three Dimensional Flow Fields Generated By The Interaction Of A Skewed Shock Wave With A Turbulent Boundary Layer 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 1975 with categories.
A detailed experimental investigation has been carried out on the three-dimensional flow fields caused by the interaction of oblique shock waves and a turbulent boundary layer. The study was performed at a free stream Mach No. of 2.95, near adiabatic wall conditions. The interaction was studied on two models having the same geometries but with different initial boundary layer thicknesses (about 0.13 and 0.55 inches). By perturbing the geometry of the experimental arrangement, it was possible to define a test region that is free of extraneous interference effects. Surface pressure measurements and oil flow patterns were obtained for both models with shock generator angles varying from 2 up to 14 deg.
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.