Download or read book An Exploratory Study of a Three Dimensional Shock Wave Boundary Layer Interaction at Mach 3 written by B. Oskam and published by . This book was released on 1975 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book An Exploratory Study of a Three dimensional Shock Wave Turbulent Boundary Layer Interaction in a Corner written by S. M. Bogdonoff and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Three dimensional Shock Wave turbulent Boundary Layer Interactions at Mach 6 written by C. Herbert Law and published by . This book was released on 1975 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Experimental Investigation of Three Dimensional Shock Wave Turbulent Boundary Layer Interaction An Exploratory Study of Blunt Fin Induced Flows written by David S. Dolling and published by . This book was released on 1980 with total page 75 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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. The emphasis in this particular study was twofold. First, the influence of incoming turbulent boundary layer thickness delta on the streamwise, spanwise and vertical scaling of the interaction was examined. Turbulent boundary layers varying in thickness from .127 cm (.05 in.) to 2.27 cm (0.89 in.) were used. In addition, a study has been conducted to examine the effects of the ratio D/delta (where D is the blunt fin leading edge diameter) on the interaction properties and scaling. Second, an investigation has been started to examine the unsteady shock wave-boundary layer structure and the resulting high frequency, large amplitude pressure fluctuations which occur ahead of and around the blunt fin leading edge. This is an area which in the past has been largely ignored, yet has important implications, since it is not clear that any mean surface property or flowfield measurements have any real physical significant. To date, measurement techniques and computer software have been developed and exploratory measurements made in the undisturbed turbulent boundary layer and also on the plane of symmetry ahead of the blunt fin.

Download or read book The Structure and Control of Three Dimensional Shock Wave Turbulent Boundary Layer Interactions written by Seymour M. Bogdonoff and published by . This book was released on 1989 with total page 39 pages. Available in PDF, EPUB and Kindle. Book excerpt: The present report briefly reviews the work accomplished on the study of three-dimensional shock wave turbulent boundary layer interactions at a Mach 3. The work consisted of two major thrusts; 1) Modeling of the complex interaction and detailed experiments coordinated with extensive computations; and 2) Exploratory studies of control concepts for a 20 deg fin and crossing shock configurations. The completed works have been reported and are briefly reviewed. A brief resume is presented of incompleted results on complex interactions, new heat transfer techniques, initial spanwise boundary layer effects, and studies in a new Low Turbulence Variable Geometry facility. Keywords: Three-dimensional shock waves; Turbulent boundary layer; Supersonic flow fields; Surface heat transfer data. (edc).

Download or read book Shock Wave Boundary Layer Interactions written by Holger Babinsky and published by Cambridge University Press. This book was released on 2011-09-12 with total page 481 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Three Dimensional Shock Wave and Turbulent Boundary Layer Interactions written by Seymour M. Bogdonoff and published by . This book was released on 1985 with total page 75 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Three dimensional Shock Wave turbulent Boundary Layer Interactions at Mach 6 written by C. Herbert Law and published by . This book was released on 1975 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Three dimensional Shock Wave turbulent Boundary Layer Interaction for a 20 Degrees Sharp Fin at Mach 3 written by B. Shapey and published by . This book was released on 1987 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Computation of Three dimensional Shock Wave and Boundary layer Interactions written by and published by . This book was released on 1985 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Three dimensional Shock Wave Boundary Layer Interaction at Mach 3 1 written by S. Bell and published by . This book was released on 1978 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of Small Surface Protuberances Upstream of Turbulent Boundary Layer Separation written by Robert H. Korkegi and published by . This book was released on 1976 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Theoretical Investigation of Three Dimensional Shock Wave Turbulent Boundary Layer Interactions Part 4 written by and published by . This book was released on 1986 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Theoretical Investigation of Three Dimensional Shock Wave Turbulent Boundary Layer Interactions written by Doyle D. Knight and published by . This book was released on 1982 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).

Download or read book Shock Wave Turbulent Boundary Layer Interactions in Two and Three Dimensions written by Gary S. Settles and published by . This book was released on 1981 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Basic experimental research was conducted in two and three-dimensional shock wave/boundary layer interactions and associated turbulence measurements. The primary emphasis has been in exploring the important but little-known range of three-dimensional interactions at high speeds. Building on previous work, a series of parametric experiments and a detailed analysis have led to the synthesis of scaling laws for Reynolds number effects on these interactions. Further experiments continued the adaptation and use of hot-wire anemometry in high-Reynolds number supersonic flows. Hot-wire surveys were made in the previously-explored flowfield of a reattaching free shear layer, and in the interaction generated by a two-dimensional compression corner of 8 deg deflection angle at Mach 3. Other research activities, including technique, instrumentation, and facility development are summarized in this report.

Download or read book Theoretical Investigation of Three Dimensional Shock Wave Turbulent Boundary Layer Interactions Part 2 written by and published by . This book was released on 1983 with total page 71 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).

Download or read book Oblique Shock Wave Turbulent Boundary Layer Interactions in Three Dimensions at Mach 3 written by B. Oskam and published by . This book was released on 1976 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).