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 1987 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: A review of the work completed during the first year of research on the subject contract is presented. Papers and publications generated, staff, and students involved in research are noted, along with a brief description of the on-going program. Significant results have been obtained in defining the structure of the three-dimensional shock wave turbulent boundary layer interaction by combining detailed experiments with coordinated major computational programs. Keywords: Shock wave, Boundary layer, Supersonic.

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 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 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 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 Investigation of Three Dimensional Shock Wave Turbulent Boundary Layer Interactions written by Morgan Lee Funderburk and published by . This book was released on 2019 with total page 325 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Theoretical Investigation of Three Dimensional Shock Wave Turbulent Boundary Layer Interactions written by D. D. Knight and published by . This book was released on 1984 with total page 52 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. This year's principle accomplishments are (1) the Baldwin-Lomax model was evaluated for a series of non-separated two-dimensional turbulent boundary layers. (2) the 3-D Navier-Stokes codes was rewritten innto CYBER 200 FORTRAN. (3) the computed results for the 3-D sharp fin alpha sub g = 10 deg were compared with the results of a separate calculation by C. Horstmann using the k-epsilon turbulence model, and the experimental data of McClure and Dolling. and (4) the 3-D sharp fin at alpha sub g =20 deg was computed, and the results compared with the available experimental data. The examination of the flowfield structure of the 3-D sharp fin at alphaa sub g = 20 deg was initiated. Originator supplied keywords include: High speed flows; Viscous-inviscid interactions; Shock-boundary layer interactions; Computational fluid dynamics; Navier-Stokes equations; and Turbulence.

Download or read book Shock Wave turbulent Boundary Layer Interaction in a Three dimensional Flow written by D. Barberis and published by . This book was released on 1995 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 The Modeling of a Three dimensional Shock Wave Turbulent Boundary Layer Interaction written by S. Bogdonoff and published by . This book was released on 1990 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 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 Theoretical Investigation of 3 D Shock Wave Turbulent Boundary Layer Interactions written by Doyle D. Knight and published by . This book was released on 1987 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: The research concerns the understanding of three dimensional shock wave turbulent boundary layer interactions. During the past year a collaborative effort has focused on theoretical and experimental investigations of the three dimensional swept compression corner at Mach 3 for compression angle of 24 deg sweep angle of 60 deg, and two different Reynolds numbers. The present author has computed the flowfield utilizing the three dimensional Reynolds averaged compressible Navier Stokes equations, with turbulence incorporated through the Baldwin Lomax algebraic turbulent eddy viscosity model. In separate efforts detailed experimental studies are performed on the flowfield, and the same configuration is computed using the Jones Launder turbulence model. The computed surface pressure profiles at the lower Reynolds number display significant disagreement with experiment. The computed surface pressure and boundary layer profiles of pitot pressure and yaw angle are in good agreement with experiment at the high Reynolds number. On the basis of detailed particle pathlines, the principal flowfield feature is observed to be a large vortical structure aligned approximately with the compression corner. This structure is qualitatively identical to the vortical structure observed for the three-dimensional sharp fin under the same external flow conditions.

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 The Study of Shock Wave and Turbulent Boundary Layer Interactions written by Seymour M. Bogdonoff and published by . This book was released on 1986 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt: The three dimensional shock wave turbulent boundary layer interaction generated by several shock generators defined solely by angles has been carried out at a Mach number of 3. Interactions with thin boundary layers were used to obtain overall characteristics, while interactions with thick boundary layers permitted detailed high resolution surveys. Investigations of the interactions were carried out by mean and high frequency surface pressure distribution measurements, surface flow visualization, and mean total head, yaw, and static pressure distributions through the flowfield. Major new data sets were obtained for the interaction of the shock wave generated by a 20 deg fin, and by a 24 deg wedge swept at 60 deg to the incoming flow. A series of tests were carried out to examine new concepts of three-dimensional interactions and extensive 'non-steady' results were obtained from the high frequency surface pressure distributions. Close coordination of the experiments with major computational efforts, support new concepts of flow structure and physics for these complex interactions. Keywords: Three-dimensional shock wave interactions; Conical similarity; Scaling laws; Conical/cylindrical boundary; Unsteady flow; Non-steady characteristics; flow physics and modeling; Supersonic characteristics.

Download or read book Three Dimensional Shock Wave Turbulent Boundary Layer Interactions A Preliminary Analysis of Blunted Fin Induced Flows written by David S. Dolling and published by . This book was released on 1977 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: An extensive experimental investigation has been made of three-dimensional blunted fin-induced shock wave turbulent boundary layer interactions. Surface pressures, heat transfer rate distributions and oil streak patterns were obtained over a range of fin bluntnesses and incidences for two different incoming boundary layers. These incoming boundary layers had mean thicknesses in the ratio of approximately 4:1. Preliminary analysis of these data indicates that, over a large region of the interaction, the property distributions collapse using purely geometric parameters. In contrast to its two-dimensional counterpart, which is a highly Reynolds number dependent viscous phenomenon, the present results seem to indicate that the three-dimensional case is primarily inviscid.

Download or read book On the Structure of Three Dimensional Shock Induced Separated Flow Regions written by R. H. Korkegi and published by . This book was released on 1982 with total page 5 pages. Available in PDF, EPUB and Kindle. Book excerpt: A study is made of existing experimental data on three-dimensional skewed shock-wave interactions with both laminar and turbulent boundary layers and recent results in which extensive regions of turbulent separation were obtained. Comparisons show that the structure of three-dimensional shock-wave/boundary-layer interactions is not fundamentally different for laminar or turbulent flow; it is primarily dependent on the extent of separation. A qualitative description is given for the flow structure from incipient to large extents of separation. For the latter, a secondary incipient condition arises within the primary separation vortex. For still larger extents of separation it is deduced that a secondary vortex arises adjacent to the surface and totally embedded in the primary separation vortex. (Author).