EBookClubs

Read Books & Download eBooks Full Online

EBookClubs

Read Books & Download eBooks Full Online

Book A Method of Calculation Compressible Turbulent Boundary Layers

Download or read book A Method of Calculation Compressible Turbulent Boundary Layers written by H. James Herring and published by . This book was released on 1968 with total page 99 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Calculation Methods for Compressible Turbulent Boundary Layers 1976

Download or read book Calculation Methods for Compressible Turbulent Boundary Layers 1976 written by Dennis M. Bushnell and published by . This book was released on 1977 with total page 156 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Evaluation of a Method for Computation of Separated Turbulent Compressible Boundary Layers

Download or read book Evaluation of a Method for Computation of Separated Turbulent Compressible Boundary Layers written by M. C. Altstatt and published by . This book was released on 1976 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computer code for a turbulent, compressible boundary-layer method, capable of carrying out computations in a region of separated flow, is developed and tested. The procedure after separation is to specify either friction velocity or boundary-layer thickness as an independent variable and obtain external velocity as a dependent variable. This requires a trial and error alternation of the specified variable in order to match the desired experimental or computed external velocity. Satisfactorily results were obtained by this method in the analysis of certain specialized cases of separated flow. (Author).

Book Approximate Formulas for the Computation of Turbulent Boundary layer Momentum Thicknesses in Compressible Flows

Download or read book Approximate Formulas for the Computation of Turbulent Boundary layer Momentum Thicknesses in Compressible Flows written by Neal Tetervin and published by . This book was released on 1946 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Approximate formulas for the computation of the momentum thicknesses of turbulent boundary layers on two-dimensional bodies, on bodies of revolution at zero angle of attack, and on the inner surfaces of round channels all in compressible flow are given in the form of integrals that can be conveniently computed. The formulas involve the assumptions that the momentum thickness may be computed by use of a boundary-layer velocity profile which is fixed and that skin-friction formulas for flat plates may be used in the computation of boundary-layer thicknesses in flow with pressure gradients. The effect of density changes on the ration of the displacement thickness to the momentum thickness of the boundary layer is taken into account. Use is made of the experimental finding that the skin-friction coefficient for turbulent flow is independent of Mach number. The computations indicated that the effect of density changes on the momentum thickness in flows with pressure gradients is small for subsonic flows.

Book FORTRAN Program for Calculating Compressible Laminar and Turbulent Boundary Layers in Arbitrary Pressure Gradients

Download or read book FORTRAN Program for Calculating Compressible Laminar and Turbulent Boundary Layers in Arbitrary Pressure Gradients written by William D. McNally and published by . This book was released on 1970 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Analysis of Turbulent Boundary Layers

Download or read book Analysis of Turbulent Boundary Layers written by Tuncer Cebeci and published by Elsevier. This book was released on 2012-12-02 with total page 423 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Book An Approximate Method for the Calculation of the Reynolds Analogy Factor for a Compressible Turbulent Boundary Layer in a Pressure Gradient

Download or read book An Approximate Method for the Calculation of the Reynolds Analogy Factor for a Compressible Turbulent Boundary Layer in a Pressure Gradient written by Neal Tetervin and published by . This book was released on 1967 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt: The method predicts that a positive pressure gradient increases and a negative pressure gradient decreases the ratio of Stanton number to friction coefficient. The Crocco relation between the velocity and total enthalpy for a non-adiabatic surface and zero pressure gradient is generalized to non-zero pressure gradient. The relation between the velocity and the total enthalpy varies markedly from the flat plate Crocco relation as the pressure gradient departs from zero. The magnitude of the variation depends on the velocity profile shape parameter. (Author).

Book Compressible Turbulent Boundary Layers

Download or read book Compressible Turbulent Boundary Layers written by and published by . This book was released on 1969 with total page 580 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book A General Method for Calculating Three dimensional Compressible Laminar and Turbulent Boundary Layers on Arbitrary Wings

Download or read book A General Method for Calculating Three dimensional Compressible Laminar and Turbulent Boundary Layers on Arbitrary Wings written by Tuncer Cebeci and published by . This book was released on 1977 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Integral Solution of Compressible Turbulent Boundary Layers Using Improved Velocity Profiles

Download or read book Integral Solution of Compressible Turbulent Boundary Layers Using Improved Velocity Profiles written by David L. Whitfield and published by . This book was released on 1978 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: A shear-work integral method is developed for calculating compressible turbulent boundary layers on planar or axisymmetric bodies. This method differs from other integral techniques primarily in the velocity profile and the velocity-temperature relation used. The velocity profile is an analytical expression that depends on the local values of skin friction, shape factor, and Reynolds number based on momentum thickness, thus no new parameters not already occurring in the integral equations are introduced. The velocity- temperature relation is also an analytical expression that describes the total- temperature overshoot near the outer edge of turbulent adiabatic wall boundary layers with nonunity Prandtl number and recovery factor. The method is fast, easy to use, and shown to provide good agreement with experimental data. The resulting computer code is relatively small. A computer program listing that is applicable to the calculation of impermeable, adiabatic wall, turbulent boundary layers for Mach numbers up to three is included.

Book A Method of Calculating Turbulent boundary layer Growth at Hypersonic Mach Numbers

Download or read book A Method of Calculating Turbulent boundary layer Growth at Hypersonic Mach Numbers written by James C. Sivells and published by . This book was released on 1959 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method is developed for calculating the growth of a turbulent boundary layer at hypersonic Mach numbers. Excellent agreement with experimental results from axisymmetric nozzles has been obtained by the application of this method. The method utilizes a modification of Stewartson's transformation to simplify the integration of the momentum equation. Heat transfer is taken into account by evaluating the gas properties at Eckert's reference temperature and by using a modification of Crocco's quadratic for the temperature distribution in the boundary layer. A new empirical relation is used for the incompressible friction coefficient which agrees with experimental data over a Reynold's number range from 10(superscript 5) to 10(superscript 9).