Laminar Separation In Supersonic Flow
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| Author | : Jean J. Ginoux |
| Publisher | : |
| Total Pages | : 75 |
| Release | : 1964 |
| Genre | : |
| ISBN | : |
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.
| Author | : Paul K. Chang |
| Publisher | : Elsevier |
| Total Pages | : 800 |
| Release | : 2014-06-28 |
| Genre | : Technology & Engineering |
| ISBN | : 1483181286 |
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 | : Jean J. Ginoux |
| Publisher | : |
| Total Pages | : 774 |
| Release | : 1960 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
| Author | : Jack Norman Nielsen |
| Publisher | : |
| Total Pages | : 92 |
| Release | : 1966 |
| Genre | : Aerodynamic heating |
| ISBN | : |
"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.
| Author | : |
| Publisher | : |
| Total Pages | : 0 |
| Release | : 1961 |
| Genre | : |
| ISBN | : |
| Author | : J. Don Gray |
| Publisher | : |
| Total Pages | : 64 |
| Release | : 1965 |
| Genre | : Laminar boundary layer |
| ISBN | : |
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.
| Author | : N. Curle |
| Publisher | : |
| Total Pages | : |
| Release | : 1960 |
| Genre | : |
| ISBN | : |
| Author | : Gary D. Kuhn |
| Publisher | : |
| Total Pages | : 89 |
| Release | : 1970 |
| Genre | : Boundary layer |
| ISBN | : |
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).
| Author | : Jean J. Ginoux |
| Publisher | : |
| Total Pages | : 1 |
| Release | : 1962 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
An experi ental investigation has been made at a Mach number of 2.21 on the effect of air injection in separated supersonic flows using two-dimensional backward facing step models. This effect, in a laminar flow, was found to be in- dependent of the particular technique of injecti n when the rate of injecti n was small. Air injection raises the base pressure and decrea es the pressure gradient at reattachment. At high rates of injection, considerable differences are found between the results obtained for various techniques of injection. It was also shown that the increase of the base-pressure is larger in the turbulent case than for a laminar boundarylayer. When freon gas was injected, it produced the opposite effect, namely of decreasing the base-pressure at low rates of injection. (Author).
| Author | : Jean J. Ginoux |
| Publisher | : |
| Total Pages | : 1 |
| Release | : 1962 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
An experimental investigation was made on laminar separated supersonic streams using two-dimensional backward-facing step models. It was shown that a cross-flow existed in the separated region of the flow which is associated with the side wall boundary-layers. Its effect is to decrease the base pressure and increase the pressure gradient at reattachment even for large values of the model-span to step-height ratio. It is shown that the commonly accepted assumption that a twodimensional flow exists when there is no measurable spanwise pressure variation is a necessary but not sufficient condition. In the turbulent case, it is generally found that the measured base pressure is lower than is theoretically predicted. This is explained by the existence of a cross-flow (suction) produced by strong vertical vortices near the side walls. (Author).
