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Author : C. Appels
Publisher :
ISBN 13 :
Total Pages : 66 pages
Book Rating : 4.F/5 ( download)
Download or read book Turbulent Boundary Layer Separation at Mach 12 written by C. Appels and published by . This book was released on 1973 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Arnold Polak
Publisher :
ISBN 13 :
Total Pages : 58 pages
Book Rating : 4.3/5 (91 download)
Download or read book The Prediction of Turbulent Boundary-layer Separation Influenced by Blowing written by Arnold Polak and published by . This book was released on 1971 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report presents an analysis predicting separation of a turbulent boundary layer over a cone-flare configuration with gas injected into the boundary layer ahead of separation point. Separation location and separation lengths are compared with experimental data obtained at Mach number of 6 and a range of Reynolds numbers. At the highest Reynolds numbers the extent of separation decreases with increasing Reynolds number. When compared to separation over cylinder-flare body it is found that the extent of separation is lower for the cone-flare configuration. (Author).
Author : William John Rainbird
Publisher :
ISBN 13 :
Total Pages : 9 pages
Book Rating : 4.:/5 (437 download)
Download or read book Turbulent Boundary Layer Growth and Separation on a Yawed 12 1/2° Cone at Mach Numbers 1.8 and 4.25 written by William John Rainbird and published by . This book was released on 1968 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : V. Zakkay
Publisher :
ISBN 13 :
Total Pages : 56 pages
Book Rating : 4.3/5 (91 download)
Download or read book Two-dimensional Turbulent Boundary Layer Separation on a Flat Plate with Ramp at Freestream Mach Numbers of 3.7 and 6.3 in Supersonic and Hypersonic Flow written by V. Zakkay and published by . This book was released on 1975 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: This investigation describes surface pressure distribution, heat transfer, and turbulent flow separation and reattachment on a flat plate with variable ramp angle at Mach numbers averaging 3.66 and 6.30. The freestream Reynold's number varied from 3.33 to 8.34 million per foot for the former case and from 5.243 million to 14.6 million per foot for the latter case. Ramp angle was varied from 0 to 35 degrees for these experiments. Stagnation temperatures averaged 849 degrees Rankine, with wall temperature assumed constant at 535 degrees Rankine for all tests. The knowledge of effective wedge angles and freestream conditions makes it possible to determine shocks so that conditions can be evaluated at all positions on the model.
Author : Larry L. Lynes
Publisher :
ISBN 13 :
Total Pages : 72 pages
Book Rating : 4.3/5 (91 download)
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.
Author : Anthony W. Fiore
Publisher :
ISBN 13 :
Total Pages : 962 pages
Book Rating : 4.3/5 (91 download)
Download or read book Boundary Layer Effects written by Anthony W. Fiore and published by . This book was released on 1978 with total page 962 pages. Available in PDF, EPUB and Kindle. Book excerpt: In 1975 the U.S. Air Force and the Federal Republic of Germany signed a Data Exchange Agreement numbered AF-75-G-7440 entitled 'Viscous and Interacting Flow Fields.' The purpose was to exchange data in the area of boundary layer research. It includes both experimental and theoretical boundary layer research at speeds from subsonic to hypersonic Mach numbers in the presence of laminar, transitional, and turbulent boundary layers. The main effort in recent years has been on turbulent boundary layers, both attached and separated in the presence of such parameters as pressure gradients, wall temperature, surface roughness, etc. In the United States the research was conducted in various Department of Defense, NASA, aircraft corporations, and various university laboratories. In the Federal Republic of Germany it was carried out within the various DFVLR, industrial, and university research centers.
Author : William J. Rainbird
Publisher :
ISBN 13 :
Total Pages : 9 pages
Book Rating : 4.:/5 (11 download)
Download or read book Turbulent Boundary Layer Growth and Separation on a Yawed 12 1/2 Degree Cone at Mach Numbers 1.8 and 4.25 written by William J. Rainbird and published by . This book was released on 1968 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Donald M. Kuehn
Publisher :
ISBN 13 :
Total Pages : 32 pages
Book Rating : 4.:/5 (31 download)
Download or read book Turbulent Boundary-layer Separation Induced by Flares on Cylinders at Zero Angle of Attack written by Donald M. Kuehn and published by . This book was released on 1961 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Paul K. Chang
Publisher : Elsevier
ISBN 13 : 1483181286
Total Pages : 800 pages
Book Rating : 4.4/5 (831 download)
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.
Author : Victor Zakkay
Publisher :
ISBN 13 :
Total Pages : 52 pages
Book Rating : 4.:/5 (227 download)
Download or read book Two-Dimensional Turbulent Boundary Layer Separation on a Flat Plate with Ramp at Freestream Mach Numbers of 3.7 and 6.3 in Supersonic and Hypersonic Flow written by Victor Zakkay and published by . This book was released on 1975 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: This investigation describes surface pressure distribution, heat transfer, and turbulent flow separation and reattachment on a flat plate with variable ramp angle at Mach numbers averaging 3.66 and 6.30. The freestream Reynold's number varied from 3.33 to 8.34 million per foot for the former case and from 5.243 million to 14.6 million per foot for the latter case. Ramp angle was varied from 0 to 35 degrees for these experiments. Stagnation temperatures averaged 849 degrees Rankine, with wall temperature assumed constant at 535 degrees Rankine for all tests. The knowledge of effective wedge angles and freestream conditions makes it possible to determine shocks so that conditions can be evaluated at all positions on the model.
Author : Robert Allan White
Publisher :
ISBN 13 :
Total Pages : 216 pages
Book Rating : 4.:/5 (31 download)
Download or read book Turbulent Boundary Layer Separation from Smooth-convex Surfaces in Supersonic Two-dimensional Flow written by Robert Allan White and published by . This book was released on 1963 with total page 216 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : William D. Harvey
Publisher :
ISBN 13 :
Total Pages : 60 pages
Book Rating : 4.:/5 (31 download)
Download or read book Fluctuating Properties of Turbulent Boundary Layers for Mach Numbers Up to 9 written by William D. Harvey and published by . This book was released on 1969 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Fluctuating properties of turbulent boundary layers for Mach numbers up to 9.
Author : Holger Babinsky
Publisher : Cambridge University Press
ISBN 13 : 1139498649
Total Pages : 481 pages
Book Rating : 4.1/5 (394 download)
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.
Author : Dudley George McConnell
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.:/5 (31 download)
Download or read book Free Flight Observation of a Separated Turbulent Flow Including Heat Transfer Up to Mach 8.5 written by Dudley George McConnell and published by . This book was released on 1960 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: A turbulent boundary layer separated by a forward-facing step was observed on the cylindrical portion of a hemisphere-cone-cylinder test vehicle. Tip blunting, producing a shear flow, was found to induce higher pressures on the cylindrical portion than were predicted from ballistic tunnel data of unblunted projectiles. An approximate method for predicting this blunt-body pressure distribution was hypothesized. These findings, along with the hypothesis, were substantiated by a wind tunnel test of a similar body. The peak pressure ratios of the separation were smaller in magnitude than flat plate theory predicted because of the effect of the shear flow. The decrement in heating of the separated flow, relative to the corresponding attached flow, was found to compare well with the expected results.
Author : James R. Sterrett
Publisher :
ISBN 13 :
Total Pages : 52 pages
Book Rating : 4.:/5 (59 download)
Download or read book Extension of Boundary-layer-separation Criteria to a Mach Number of 6.5 by Utilizing Flat Plates with Forward-facing Steps written by James R. Sterrett and published by . This book was released on 1960 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation has been made of the separation phenomena on a flat plate to which forward-facing steps were attached to force separation. Both laminar and turbulent flows were investigated over a Mach number range of approximately 4 to 6.5. By using pressure distribution, shadowgraph and chemical film techniques, the pressure rise at separation, the laminar plateau pressure and the turbulent peak pressure were determined. Boundary-layer surveys were made on a smooth flat plate and on a flat plate with roughness to force transition. Examinations of the separated flow showed that the predominant variable in the determination of the pressure distribution was the location of transition relative to the generation point and reattachment. Pure laminar, transitional and turbulent types of separation were found in this Mach number range. The peak static-pressure-rise ratios for identical forward-facing steps at a Mach number of 6.25 were approximately 1.5 and 5.0, respectively, for pure laminar and turbulent separation. The effect of Reynolds number on the peak pressure rise for turbulent separation for the low Mach number range was found to be very minor provided the step height was of the order of the bounday-layer thickness. As the Mach number is increased, the peak pressure coefficient C(p, p) for turbulent separation decreased from approximately 0.18 at a Mach number of 4 to about 0.13 at a Mach number of 6.25. The pressure coeeficient at the separation point for laminar separation decreases from approximately 0.014 at a Mach number of 4 to approximately half that value at a Mach number of 6.5. The results obtained with forward-facing steps agree with the trend predicted, based upon lower Mach number studies.
Author : Hermann F. Fasel
Publisher :
ISBN 13 :
Total Pages : 90 pages
Book Rating : 4.3/5 (91 download)
Download or read book Control of Separation for Turbulent Boundary Layers Subjected to Wall Curvature and Streamwise Pressure Gradients written by Hermann F. Fasel and published by . This book was released on 2005 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : P. Doerffer
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book Mach Number Dependence of Flow Separation Induced by Normal Shock Wave/turbulent Boundary Layer Interaction at a Curved Wall written by P. Doerffer and published by . This book was released on 1989 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
