Download or read book Separation of Flow written by Paul K. Chang and published by Elsevier. This book was released on 2014-06-28 with total page 800 pages. Available in PDF, EPUB and Kindle. Book excerpt: Interdisciplinary and Advanced Topics in Science and Engineering, Volume 3: Separation of Flow presents the problem of the separation of fluid flow. This book provides information covering the fields of basic physical processes, analyses, and experiments concerning flow separation. Organized into 12 chapters, this volume begins with an overview of the flow separation on the body surface as discusses in various classical examples. This text then examines the analytical and experimental results of the laminar boundary layer of steady, two-dimensional flows in the subsonic speed range. Other chapters consider the study of flow separation on the two-dimensional body, flow separation on three-dimensional body shape and particularly on bodies of revolution. This book discusses as well the analytical solutions of the unsteady flow separation. The final chapter deals with the purpose of separation flow control to raise efficiency or to enhance the performance of vehicles and fluid machineries involving various engineering applications. This book is a valuable resource for engineers.
Download or read book LAMINAR SEPARATION IN SUPERSONIC FLOW written by Jean J. Ginoux and published by . This book was released on 1964 with total page 75 pages. Available in PDF, EPUB and Kindle. Book excerpt: Detailed experimental investigations were made at a Mach number of 2.21 of laminar flows over ramps, backward facing steps and swept back wings. Large spanwise variations of the heat transfer coefficient (h) were measured, with two different techniques, in the reattachment region of the flow over a backward facing step and were related to streamwise vortices present in the laminar boundary layer. Peaks in h much larger than the turbulent value were measured. By comparing spanwise total head and heat transfer rate distributions, Reynolds analogy was found to apply quantitatively for reattaching flows with streamwise vortices. The effect of free-stream Reynolds number and of leading edge sweep, accuracy of machining, thickness and bevel angle on the intensity of streamwise vortices present in the boundary layer on swept back wings was investigated. Flow separation was detected at the leading edge. A regular pattern of streamwise vortices of small wave length was observed outside of the boundary layer.
Download or read book Calculation of Laminar Separation with Free Interaction by the Method of Integral Relations written by Jack Norman Nielsen and published by . This book was released on 1966 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: "A calculative method is presented for determining separated, laminar, boundary-layer characteristics from in front of the separation point to the reattachment point under the influence of 'free interaction' between the main flow and the boundary layer. The analysis covers supersonic flow over two-dimensional and axisymmetric configurations with adiabatic or nonadiabatic wall conditions. For nonadiabatic wall conditions, theories based on first-order coupling and second-order coupling between velocity and total temperature profiles were presented. The theory based on first-order coupling was included in a machine calculation program with options for two-dimensional or axisymmetric flow and adiabatic or nonadiabatic wall conditions. Extensive systematic calculations were made to determine the range of possible separated flows over a two-dimensional configuration as a function of separation point location and wall temperatures. Comparison between experiment and theory for separation pressure distributions on two-dimensional or axisymmetric adiabatic configurations shows generally good agreement. Good comparison between experiment and theory is indicated for a moderately-cooled axisymmetric configuration. For a highly-cooled axisymmetric configuration, the prediction of the machine program based on first-order coupling is inadequate, indicating the necessity for a higher-order coupling theory." -- page iii.
Download or read book Laminar Separation in Supersonic Flow with Emphasis on Three dimensional Perturbations at Reattachment written by Jean J. Ginoux and published by . This book was released on 1960 with total page 774 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Laminar Boundary layer Separation on Flared Bodies at Supersonic and Hypersonic Speeds written by J. Don Gray and published by . This book was released on 1965 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experiments at supersonic speeds and at Mach 8 were conducted to determine the conditions which govern the extent of shock-induced laminar flow separations on axisymmetric configurations at zero yaw and without heat transfer. From an extensive correlation of surface pressure data and schlieren photographs, it is shown that the extent of reverse flow is essentially a function of the ratio of the wetted length to the flare divided by the laminar boundary thickness there. As a result, the relative extent of laminar flow separation decreases with a unit Reynolds number increase and grows through an increase in Mach number. Finally, increasing the flare angle increases the length of the reverse flow region.
Download or read book Preliminary Report on a Study of Separated Flows in Supersonic and Subsonic Streams written by Dean R. Chapman and published by . This book was released on 1956 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Some results are described of fundamental research conducted on various flow separation phenomena in two-dimensional streams. Experimental and theoretical results are described for the pressure rise across a reattachment region, and for the Reynolds number dependence of the pressure rise to a separation point. Observations are made throughout of the location of transition relative to reattachment and to separation, since this relative location turned out to be the dominant variable investigated.
Download or read book Leading Edge Effect on Separated Supersonic Flows Contract Nr AF 61 052 350 written by and published by . This book was released on 1961 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Current Papers written by and published by . This book was released on 1950 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Turbulent Shear Layers in Supersonic Flow written by Alexander J. Smits and published by A I P Press. This book was released on 1996 with total page 384 pages. Available in PDF, EPUB and Kindle. Book excerpt: Using the most recent data, this text describes the physical mechanisms of turbulent supersonic flows, emphasizing the similarities and differences between compressible and incompressible flows. DLC: Aerodynamics, Supersonic.
Download or read book The Effects of Heat Transfer on Laminar boundary layer Separation in Supersonic Flow written by N. Curle and published by . This book was released on 1960 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Inhibition of Flow Separation at High Speed written by Larry L. Lynes and published by . This book was released on 1969 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: The method of integral relations was successfully applied to compressible nonadiabatic turbulent boundary layers on a flat plate. The theory is designed to accept any desired eddy-viscosity model. A particular eddy-viscosity model was incorporated into the method, and the equations were programmed for application to a flat plate with no pressure gradient. The variations of the skin-friction coefficient with Reynolds number, Mach number, and temperature ratio were calculated using this program, and the results are in good accord with similar results calculated by the Spalding-Chi method and the Rubesin T' method. An analysis was made to predict to what extent turbulent separation of the free-interaction type can be inhibited by means of surface cooling. It was observed experimentally that free-interaction is applicable to separated turbulent boundary layers up to the separation point or beyond. The free-interaction model used in the analysis is based on adding the boundary-layer displacement thickness to the actual body dimensions in calculating the induced pressures. The critical temperature ratios calculated on this basis are generally greater than adiabatic wall temperature except in the supersonic range up to a Mach number approaching 3, where moderate cooling is required to inhibit separation.
Download or read book Prediction of Supersonic Laminar Flow Separation by the Method of Integral Relations with Free Interaction written by Gary D. Kuhn and published by . This book was released on 1970 with total page 89 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report describes the development of a predictive method for calculating separated laminar boundary layers on flat-plate-wedge and cylinder-flare configurations in supersonic flow and the application of the method to predicting the effects of Mach number, Reynolds number, and temperature ratio on the properties of the boundary layer. The purpose of the report is to extend previous analytical work employing the method of integral relations to the region downstream of reattachment and to describe an interative technique developed to produce a unique solution. The theory is shown to produce good comparisons with pressure data on flat-plate-wedge configurations for both adiabatic and cold walls. Accounting for non-Blasius initial velocity profiles produced by favorable pressure gradients upstream of the beginning of interaction was shown to decrease the predicted extent of separation. For axisymmetric configurations the length of an equivalent cylinder must be calculated by an auxiliary method. Good to fair comparisons with experimental pressure distributions were produced by adjusting the equivalent cylinder length. Fair comparison was produced between the theory and experimental heat-transfer rate data on an ogive-cylinder-flare configuration. The theory is shown to predict an incipient separation wedge angle which agrees reasonably well with experimental results. (Author).
Download or read book Laminar Boundary Layer on a Circular Cone in Supersonic Flow at a Small Angle of Attack written by Franklin K. Moore and published by . This book was released on 1951 with total page 710 pages. Available in PDF, EPUB and Kindle. Book excerpt: The laminar boundary layer on a circular cone at angle of attack to a supersonic stream is discussed. A perturbation analysis was made to show the influence of a small angle of attack on such boundary layer quantities as skin friction, boundary-layer thickness, viscous lift, drag, and pitching moment.
Download or read book Flow Separation Ahead of Blunt Bodies at Supersonic Speeds written by Wolfgang E. Moeckel and published by . This book was released on 1951 with total page 668 pages. Available in PDF, EPUB and Kindle. Book excerpt: Supersonic flow against blunt bodies placed in boundary layers is discussed, and it is concluded that wedge-shaped or conical dead-air regions should form ahead of the body for some ranges of body thickness. Analysis of this type of flow indicates that a maximum body thickness exists (relative to initial boundary-layer thickness) beyond which steady wedge-type or conical separation regions cannot occur. For the range of relative body thicknesses for wihch wedge-type separation occurs, good agreement was obtained between experimental and theoretical pressures in the dead-air region at Mach numbers from 1.73 to 2.02. Unsteady flow was obtained for large relative body thickness.
Download or read book Supersonic Separated Flows Over Wedges and Flares with Emphasis on a Method of Detecting Transition written by Jean J. Ginoux and published by . This book was released on 1968 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: The investigation is a first step to the study of the effect of cross flow in laminar separation at supersonic speeds. It is related to the selection of a final axi-symmetric model. Several problems were examined. First, the effect of streamwise vortices that develop systematically in laminar reattaching flows, triggered by small irregularities in the leading edge thickness. Second, the choice of the diameter of the model such that the flow resembles that of an equivalent planar body, third the programming of Lees-Reeves theory on a 1130 IBM computer to perform a parametric study and finally the development of a new accurate technique or criteria to ascertain that fully laminar shock wave boundary layer interactions can be obtained. (Author).
Download or read book Transition Reynolds Numbers of Separated Flows at Supersonic Speeds written by Howard K. Larson and published by . This book was released on 1960 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental research has been conducted on the effects of wall cooling, Mach number, and unit Reynolds number on the transition Reynolds number of cylindrical separated boudary layers on an ogive-cylinder model. Results were obtained from pressure and temperature measurements and shadowgraph observations. The maximum scope of measurements encompassed Mach numbers between 2.06 and 4.24, Reynolds numbers (based on length of separation) between 60,000 and 400,000, and ratios of wall temperatures to adiabatic wall temperature between 0.35 and 1.0.
Download or read book Supersonic Laminar Boundary Layer Flow Past a Wavy Wall with Multiple Separation Regions written by A. Polak and published by . This book was released on 1975 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Laminar flow over wave shaped walls with multiple separation bubbles were studied using an implicit finite difference technique. Solutions are presented for Mach 3 and 6, Re 100 000 and 200 000, Tw/To = 0.45, and 0.675 and protuberance height to width ratio from 0 to 0.1. Results are compared with empirical correlations and experimental data.
