Turbulent boundary layer velocity profiles in supersonic flow along a flat plate
Author : Donald Richardson Buell
Publisher :
Page : 60 pages
File Size : 12,88 MB
Release : 1950
Category : Boundary layer
ISBN :
Turbulent Boundary-layer Velocity Profiles on a Nonadiabatic Flat Plate at Mach Number 6.5
Author : Earl R. Keener
Publisher :
Page : 60 pages
File Size : 14,68 MB
Release : 1972
Category : Aerodynamics, Hypersonic
ISBN :
Book Description
Velocity profiles were obtained from pitot-pressure and total-temperature measurements within a turbulent boundary layer on a large sharp-edged flat plate. Momentum-thickness Reynolds number ranged from 2590 to 8860 and wall-to-adiabatic-wall temperature ratios ranged from 0.3 to 0.5. Measurements were made both with and without boundary layer trips. Five methods are evaluated for correlating the measured velocity profiles with the incompressible law-of-the-wall and the velocity defect law. The mixing-length generalization of Van Driest gives the best correlation.
Turbulent Shear Layers in Supersonic Flow
Author : Alexander J. Smits
Publisher : Springer Science & Business Media
Page : 418 pages
File Size : 17,67 MB
Release : 2006-05-11
Category : Science
ISBN : 0387263055
Book Description
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.
Turbulent Boundary-layer Temperature Recovery Factors in Two-dimensional Supersonic Flow
Author : Maurice Tucker
Publisher :
Page : 30 pages
File Size : 33,98 MB
Release : 1951
Category : Aerodynamics, Supersonic
ISBN :
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.
Power-law Velocity-profile-exponent Variations with Reynolds Number, Wall Cooling, and Mach Number in a Turbulent Boundary Layer
Author : Charles Borden Johnson
Publisher :
Page : 66 pages
File Size : 33,6 MB
Release : 1969
Category : Reynolds number
ISBN :
Book Description
Separation of Flow
Author : Paul K. Chang
Publisher : Elsevier
Page : 800 pages
File Size : 14,76 MB
Release : 2014-06-28
Category : Technology & Engineering
ISBN : 1483181286
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.
Turbulent Boundary Layer Characteristics at High Reynolds Number
Author : V. Zakkay
Publisher :
Page : 56 pages
File Size : 17,82 MB
Release : 1975
Category : Aerodynamics, Supersonic
ISBN :
Book Description
The pressure gradient effect on the characteristics of a compressible turbulent boundary layer in separation and reattachment regions of laminar and turbulent flows have been investigated. Experiments were conducted at a large variation of Mach numbers and free stream Reynolds numbers. Favorable pressure gradient was found to have significant effect on the correlation of the total temperature and velocity profiles in turbulent boundary layer. Correlations for the separation distance, peak heating values, and peak surface pressure were found. Methods are described to predict the location and peak heating values in a separated flow region.
Turbulent-boundary-layer Characteristics of Pointed Slender Bodies of Revolution at Supersonic Speeds
Author : Jerry M. Allen
Publisher :
Page : 114 pages
File Size : 29,27 MB
Release : 1967
Category : Cone
ISBN :
Book Description
Boundary-layer Theory
Author : Hermann Schlichting
Publisher :
Page : 784 pages
File Size : 39,85 MB
Release : 1968
Category : Science
ISBN :
Book Description
This text is the translation and revision of Schlichting's classic text in boundary layer theory. The main areas covered are laws of motion for a viscous fluid, laminar boundary layers, transition and turbulence, and turbulent boundary layers.
Inhibition of Flow Separation at High Speed
Author : Larry L. Lynes
Publisher :
Page : 72 pages
File Size : 44,48 MB
Release : 1969
Category : Aerodynamics, Supersonic
ISBN :
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.
