Separation of a Subsonic Turbulent Boundary Layer
| Author | : S. M. Bogdonoff |
| Publisher | : |
| Total Pages | : 46 |
| Release | : 1954 |
| Genre | : |
| ISBN | : |
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Separation Of A Subsonic Turbulent Boundary Layer
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Experimental Study on High Subsonic Turbulent Flow Incipient Separation
| Author | : Jain-Ming Wu |
| Publisher | : |
| Total Pages | : 68 |
| Release | : 1976 |
| Genre | : Aerodynamics |
| ISBN | : |
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For flow over a two-dimensional ramp compression corner case, an experimental investigation to determine the incipient separation was carried out at Mach numbers between 0.55 and 0.9 and Reynolds numbers (based on undisturbed boundary layer thickness) between 350,000 and 690,000. Detailed surface pressure, pitot traversing and oil flow data were obtained for each ramp angle case. Two-dimensionality of the ramp compression corners was verified by the surface oil flow. A major finding of this study is that the incipient separation ramp angle is relatively independent of Mach number and Reynolds number within the range studied. The incipient separation ramp angle was found to be about 22.5 degrees.
Study on High Subsonic Turbulent Flow Incipient Separation and Hole/boundary Layer Interaction
| Author | : Hideki Kuwano |
| Publisher | : |
| Total Pages | : 98 |
| Release | : 1976 |
| Genre | : |
| ISBN | : |
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Development of a Method for Predicting Subsonic Turbulent Separating Boundary Layers
| Author | : Philip M. Gerhart |
| Publisher | : |
| Total Pages | : 171 |
| Release | : 1978 |
| Genre | : |
| ISBN | : |
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An attempt is made to develop a method for predicting subsonic flows exhibiting pressure gradient induced turbulent boundary layer separation. The concept of a strong interaction between rotational (viscous) layer near a body and an external irrotational flow is adopted. The boundary layer approximations to the equations of motion are retained in the viscous layer; mathematical coupling between the flow regions is introduced by requiring continuity of flow speed (or Mach number) and direction. An integral method is used to solve the boundary layer equations; the equations are set up so that either flow speed or angle can be calculated, given the other. A modification of the wall-wake velocity profile valid for compressible flow is used together with an algebraic non-equilibrium turbulence model. Equations solved are the integral continuity, momentum, and moment of momentum equations. Predictions for compressible and incompressible plane two-dimensional separating and reattaching boundary layers are quite good when edge speed or angle are available from experimental data.
Separation of Flow
| Author | : Paul K. Chang |
| Publisher | : Elsevier |
| Total Pages | : 800 |
| Release | : 2014-06-28 |
| Genre | : Technology & Engineering |
| ISBN | : 1483181286 |
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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.
Stability of Separating Subsonic Boundary Layers
| Author | : Jamal A. Masad |
| Publisher | : |
| Total Pages | : 56 |
| Release | : 1994 |
| Genre | : |
| ISBN | : |
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Boundary Layer Effects
| Author | : Anthony W. Fiore |
| Publisher | : |
| Total Pages | : 962 |
| Release | : 1978 |
| Genre | : Turbulent boundary layer |
| ISBN | : |
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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.
Some Fluid Mechanical Problems Related to Subsonic and Supersonic Aircraft
| Author | : United States. National Aeronautics and Space Administration. Ad Hoc Committee on Subsonic and Supersonic Aeronautics |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1968 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
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Stability of Separating Subsonic Boundary Layers
| Author | : Jamal Ahmad Masad |
| Publisher | : |
| Total Pages | : 56 |
| Release | : 1994 |
| Genre | : Boundary layer |
| ISBN | : |
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Turbulent Shear Layers in Supersonic Flow
| Author | : Alexander J. Smits |
| Publisher | : Springer Science & Business Media |
| Total Pages | : 418 |
| Release | : 2006-05-11 |
| Genre | : Science |
| ISBN | : 0387263055 |
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A good understanding of turbulent compressible flows is essential to the design and operation of high-speed vehicles. Such flows occur, for example, in the external flow over the surfaces of supersonic aircraft, and in the internal flow through the engines. Our ability to predict the aerodynamic lift, drag, propulsion and maneuverability of high-speed vehicles is crucially dependent on our knowledge of turbulent shear layers, and our understanding of their behavior in the presence of shock waves and regions of changing pressure. Turbulent Shear Layers in Supersonic Flow provides a comprehensive introduction to the field, and helps provide a basis for future work in this area. Wherever possible we use the available experimental work, and the results from numerical simulations to illustrate and develop a physical understanding of turbulent compressible flows.
