A Numerical Study of Separating Supersonic Laminar Boundary-layers PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download A Numerical Study of Separating Supersonic Laminar Boundary-layers PDF full book. Access full book title A Numerical Study of Separating Supersonic Laminar Boundary-layers by G. D. Senechal. Download full books in PDF and EPUB format.
Author: G. D. Senechal
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 61
Get Book Here
Book Description
A numerical study has been made of the nature of the solution to the supersonic boundary-layer equations when the flow separates from the surface. To this end, implicit finite difference solutions t the governing equations are obtained for linearly and quadratically retarded flows over flat plates for a Mach number range of 2 to 15. Both extremely hot and cold wall conditions are considered. Also, solutions for flow on a compression ramp are obtained with and without including the boundary layer's free interaction with the local freestream. The results of this study indicate that non-interacting flows are singular at separation and that free interaction effects reduces singularity. An alternate means of numerically smearing out the singularity and proceeding past separation is also presented.
Author: G. D. Senechal
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 61
Get Book Here
Book Description
A numerical study has been made of the nature of the solution to the supersonic boundary-layer equations when the flow separates from the surface. To this end, implicit finite difference solutions t the governing equations are obtained for linearly and quadratically retarded flows over flat plates for a Mach number range of 2 to 15. Both extremely hot and cold wall conditions are considered. Also, solutions for flow on a compression ramp are obtained with and without including the boundary layer's free interaction with the local freestream. The results of this study indicate that non-interacting flows are singular at separation and that free interaction effects reduces singularity. An alternate means of numerically smearing out the singularity and proceeding past separation is also presented.
![A Numerical Study of Seperating Supersonic Laminar Boundary-layers [by] G. D. Senechal and M. J. Werle PDF](https://books.google.com/books/content/images/frontcover/KPydwgEACAAJ?fife=w80-h100)
Author: G D. Senechal
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 61
Get Book Here
Book Description
Author: Jack Norman Nielsen
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 92
Get Book Here
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.
Author: Paul K. Chang
Publisher: Elsevier
ISBN: 1483181286
Category : Technology & Engineering
Languages : en
Pages : 800
Get Book Here
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.
Author: Larry L. Lynes
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 72
Get Book Here
Book Description
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: M. J. Werle
Publisher:
ISBN:
Category :
Languages : en
Pages : 118
Get Book Here
Book Description
An efficient numerical solution algorithm is presented for solving the interacting supersonic laminar boundary layer problem. The method employs a time dependent approach with the alternating direction implicit (ADI) scheme and directly accounts for the necessary downstream boundary condition. Solutions are presented for (M sub infinity) = 3 cold wall boundary layer flow over a family of expansion and compression ramps including several cases with regions of reverse flow. Good comparison is given with experimental data and Navier Stokes solutions for (M sub infinity) = 4, adiabatic wall, separated flow up a ten degree compression ramp. (Author).
Author: Milton Van Dyke
Publisher: Parabolic Press, Incorporated
ISBN:
Category : Science
Languages : en
Pages : 296
Get Book Here
Book Description
Author: Gary W. Huband
Publisher:
ISBN:
Category :
Languages : en
Pages : 85
Get Book Here
Book Description
The purpose of this work was to obtain the solution to three supersonic flow problems using three different numerical techniques. First, a shock/boundary layer problem is solved using MacCormack's explicit technique. Then, using the same technique a shrouded rocket nozzle problem is solved. These two problems showed that the explicit scheme required many minutes of computer time to solve. In order to explore more efficient codes to solve the shroud problem, space marching algorithms were studied. A space marching algorithm using flux-splitting in the streamwise direction was applied to an approximate form of the Navier-Stokes equation. Flux-splitting combined with a global interation approach should allow the shroud problem to be solved with a space marching algorithm. The flux-splitting code was applied to two supersonic flow problems and very good results were obtained. (Author) (Theses).
Author: S. C. Holmes
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
Get Book Here
Book Description
