Download or read book An Exploratory Study of Corner Bleed on a Fin Generated Three dimensional Shock Wave Turbulent Boundary Layer Interaction written by A. Steven Toby and published by . This book was released on 1989 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 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 Theoretical Investigation of 3 D Shock Wave turbulent Boundary Layer Interactions written by Doyle D. Knight and published by . This book was released on 1988 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1993 with total page 992 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book 93 2965 93 2999 written by and published by . This book was released on 1993 with total page 594 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book AIAA 22nd Fluid Dynamics Plasma Dynamics Lasers Conference 91 1752 91 1779 written by and published by . This book was released on 1991 with total page 410 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 1988 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: The research concerns the understanding of 3-D shock wave-turbulent boundary layer interactions. The research activity has focused on several areas. First, the 3-D swept compression corner has been computed at Mach 3 for a sweep angle of 40 deg and compression angle of 24 deg. The calculated flows are in good agreement with experiment. Second, the flowfield structure of the 3-D swept compression corner is dominated by a large vortical structure. Third, the interaction has been found quantitatively to be dominated by inviscid effects except within a small fraction of the boundary layer. Fourth, the effect of boundary layer bleed has been examined for the 3-D shock wave-turbulent boundary layer interaction generated by a sharp fin. The effects of bleed are principally limited to the near surface region. The overall vortical structure is insensitive to surface bleed. Keywords: High speed flows; Viscous-inviscid interactions; Computational fluid dynamics; Navier-Stokes equations.
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 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 A Numerical Investigation of 3 D Shock Wave turbulent Boundary Layer Interactions Generated by the Sharp Fin and Swept Compression Corner written by Yan Zang and published by . This book was released on 1988 with total page 332 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 AIAA 27th Aerospace Sciences Meeting written by and published by . This book was released on 1989 with total page 476 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of Laminar and Turbulent Boundary Layers Interacting with Externally Generated Shock Waves written by Earl C. Watson and published by . This book was released on 1969 with total page 140 pages. Available in PDF, EPUB and Kindle. Book excerpt: Laminar and turbulent boundary layer interactions with externally generated shock waves.
Download or read book NASA SP written by and published by . This book was released on 1990 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 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 published by . This book was released on 1980 with total page 61 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. 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).
