Download or read book An Experimental Investigation of a Three dimensional Shock Wave boundary Layer Interaction written by Wei-Ming Keng and published by . This book was released on 1980 with total page 250 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of a Three dimensional Shock Wave turbulent Boundary Layer Interaction in Supersonic Flow written by John Warren Welch and published by . This book was released on 1987 with total page 348 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 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 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 Experimental Study of Shock wave Boundary layer Interaction in a Three dimensional Channel Flow written by R. Benay and published by . This book was released on 1985 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Study of Three dimensional Shock Wave Boundary Layer Interactions Generated by Sharp Fins written by Frank K. Lu and published by . This book was released on 1983 with total page 306 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 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 Experimental and Analytical Investigation of Transonic Shock wave boundary layer Interaction Control with Three dimensional Bumps written by Hideaki Ogawa and published by . This book was released on 2007 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book 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 published by . This book was released on 1975 with total page 225 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Velocity Measurements in a 3D Three Dimensional Shock Wave Laminar Boundary Layer Interaction written by G. Degrez and published by . This book was released on 1987 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the three dimensional laminar boundary layer separation associated with an incident swept shock wave was conducted in the von Karman Institute (VKI) S-1 supersonic wind tunnel operating at Mach 2.15. Mean velocity profiles were measured both in the attached separated and reattachment flow regions using a laser doppler velocimeter. A comparison of the measurements with a full 3D Navier-Stokes solver, developed at the VKI, exhibited good agreement in all three regions, thus validating the code which was based on the Beam-Warming algorithm. The report also reviews the earlier parts of the grant dealing with the necessary developments in LDV to achieve high quality data, and the of the 2D shock boundary layer interaction. Keywords: Two dimensional flow; Three dimensional flow; Laminar boundary layer; Flow separation.
Download or read book An Experimental Investigation of the Shock Wave turbulent Boundary Layer Interaction written by David William Kuntz and published by . This book was released on 1985 with total page 544 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An experimental investigation of shock wave turbulent boundary layer interactions with and without boundary layer suction written by Chen-Chih Sun and published by . This book was released on 1977 with total page 916 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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).
Download or read book An Experimental Investigation of Shock Wave turbulent Boundary Layer Interactions with and Without Boundary Layer Suction written by C. C. Sun and published by . This book was released on 1977 with total page 916 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tabulated data from a series of experimental studies of the interaction of a shock wave with a turbulent boundary layer in axisymmetric flow configurations is presented. The studies were conducted at the walls of circular wind tunnels and on the cylindrical centerbody of an annular flow channel. Detailed pitot pressure profiles and wall static pressure profiles upstream of, within and downstream of the interaction region are given. Results are presented for flows at nominal freestream Mach Numbers of 2, 3 and 4. For studies at the tunnel sidewalls, the shock waves were produced by conical shock generators mounted on the centerline of the wind tunnel at zero angle of attack. The annular ring generator was used to produce the shock wave at the centerbody of the annular flow channel. The effects of boundary layer bleed were examined in the investigation. Both bleed rate and bleed location were studied. Most of the bleed studies were conducted with bleed holes drilled normal to the wall surface but the effects of slot suction were also examined. A summary of the principal results and conclusions is given.
Download or read book An Experimental Investigation Into the Shock Wave boundary Layer Interaction on a 6 wedge written by Carl M. Putnam and published by . This book was released on 1991 with total page 198 pages. Available in PDF, EPUB and Kindle. Book excerpt:
