Author: Aeronautical Research CouncilPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 8
Book Description
Boundary Layer Separation in Two-dimensional Supersonic Flow
Author: Aeronautical Research CouncilPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 8
Book Description
Boundary Layer Separation in Two-dimensional Supersonic Flow
Author: Aeronautical Research CouncilPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 8
Book Description
Separation of Flow
Author: Paul K. ChangPublisher: Elsevier
ISBN: 1483181286
Category : Technology & Engineering
Languages : en
Pages : 800
Book Description
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.
Calculation of Laminar Separation with Free Interaction by the Method of Integral Relations
Author: Jack Norman NielsenPublisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 92
Book Description
"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.
Incipient Separation of a Turbulent Boundary Layer at High Reynolds Number in Two- Dimensional Supersonic Flow Over a Compression Corner
Author: Turbulent Boundary Layer Separation from Smooth-convex Surfaces in Supersonic Two-dimensional Flow
Author: Robert Allan WhitePublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 216
Book Description
Turbulent Boundary-layer Temperature Recovery Factors in Two-dimensional Supersonic Flow
Author: Maurice TuckerPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 30
Book Description
An analytical method is presented for obtaining turbulent temperature recovery factors for a thermally insulated surface in supersonic flow. The method is an extension of Squire's analysis for incompressible flow. The boundary layer velocity profile is represented by a power law and a similarity is postulated for squared-velocity the static-temperature-difference profiles.
Experimental Investigation of the Pressure Rise Required for the Incipient Separation of Turbulent Boundary Layers in Two-dimensional Supersonic Flow
Author: Donald M. KuehnPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 48
Book Description
Three Dimensional Boundary Layer Separation in Supersonic Flow
Author: W. D. BachaloPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 174
Book Description
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
Author: V. ZakkayPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 56
Book Description
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.