Flow Properties of Compressible and Imcompressible Subsonic Turbulent Boundary Layers with Surface Roughness PDF Download
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Author: Victor E. Pritchett
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Victor E. Pritchett
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Donald E. Coles
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 580
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Book Description
The first object of the paper is to develop a transformation which reduces the boundary-layer equations for compressible two-dimensional mean turbulent motion to incompressible form. The second object is to apply this transformation to the special case of the adiabatic turbulent boundary layer on a smooth wall. The transformation represents at every stage a genuine kinematic and dynamic correspondence between two real flows, both of which are capable of being observed experimentally. Since the mean pressure and mean velocity can then be measured in either flow, the mean acceleration of the fluid can in principle be determined, and the shearing stress can be adequately and accurately defined as the stress which is necessary to account for this acceleration. This formulation leads to a general transformation valid for laminar or turbulent flow in wakes and boundary layers, without regard to the state or energy equations or the viscosity law for the compressible fluid, and without regard to the boundary conditions on surface pressure or temperature in the event that a surface is involved. (Author).
Author: Tuncer Cebeci
Publisher: Elsevier
ISBN: 0323151051
Category : Technology & Engineering
Languages : en
Pages : 423
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Book Description
Analysis of Turbulent Boundary Layers focuses on turbulent flows meeting the requirements for the boundary-layer or thin-shear-layer approximations. Its approach is devising relatively fundamental, and often subtle, empirical engineering correlations, which are then introduced into various forms of describing equations for final solution. After introducing the topic on turbulence, the book examines the conservation equations for compressible turbulent flows, boundary-layer equations, and general behavior of turbulent boundary layers. The latter chapters describe the CS method for calculating two-dimensional and axisymmetric laminar and turbulent boundary layers. This book will be useful to readers who have advanced knowledge in fluid mechanics, especially to engineers who study the important problems of design.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 892
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Author: John Laufer
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 13
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Book Description
A qualitative discussion is given on compressibility effects on turbulence. An attempt is made to extract the main features of supersonic and hypersonic turbulent boundary layers from the information available and to examine the calculation techniques and transformation methods used for predicting behavior. These predictions include estimations of mean velocity and temperature distribution. In the absence of a theory for compressible or even incompressible turbulent boundary layers, most analytical studies approach the problem by reducing it essentially to the problem of an incompressible fluid. A critical examination is made in terms of both the direct approach and the transformation method. Finally, some experiments are recommended to help generate a more consistent empirical formulation of the hypersonic boundary layer problem and improve present methods of measurement regarding mean velocity and mean temperature distributions. (Author).
Author: Virgil A. Sandborn
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 168
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Author: Fred Culick
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 80
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Author: David L. Brott
Publisher:
ISBN:
Category : Compressibility
Languages : en
Pages : 104
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Book Description
The paper describes the results of a detailed experimental investigation of a two-dimensional turbulent boundary layer in a favorable pressure gradient where the free-stream Mach number varied from 3.8 to 4.6 and the ratio of wall to adiabatic-wall temperature has a nominal value of 0.82. Detailed profile measurements were made with pressure and temperature probes; skin friction was measured directly with a shear balance. The velocity- and temperature-profile results were compared with zero pressure gradient and incompressible results. The skin-friction data were correlated with momentum-thickness Reynolds number and pressure-gradient parameter. (Author).
Author: Walter B. Sturek
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 32
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Book Description
A numerical study has been performed using a finite-difference boundary layer computer program that includes corrections to the equations of motion for longitudinal curvature and allows the static pressure to be specified as a known function of x and y. Calculations with and without the corrections for longitudinal curvature and pressure gradient normal to be the local surface have been compared to experimental measurements of a supersonic turbulent boundary layer flow over a surface with concave longitudinal curvature. Substantially improved agreement with experimental measurements is obtained for the calculations including corrections for wall curvature and pressure gradient normal to the local surface for density profile, skin friction coefficient, and boundary-layer integral properties.
Author: Klaus Oswatitsch
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 68
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Book Description
Summary: The present report consists of two parts. The first part deals with the two-dimensional stationary flow in the presence of local supersonic zones. A numerical method of integration of the equation of gas dynamics is developed. Proceeding from solutions at great distance from the body the flow pattern is calculated step by step. Accordingly the related body form is obtained at the end of the calculation. The second part treats the relationship between the displacement thickness of laminar and turbulent boundary layers and the pressure distribution at high speeds. The stability of the boundary layer is investigated, resulting in basic differences in the behavior of subsonic and supersonic flows. Lastly, the decisive importance of the boundary layer for the pressure distribution, particularly for thin profiles, is demonstrated.
