Calculation Methods for Compressible Turbulent Boundary Layers, 1976
Author : Dennis M. Bushnell
Publisher :
Page : 156 pages
File Size : 48,57 MB
Release : 1977
Category : Compressibility
ISBN :
Author : Dennis M. Bushnell
Publisher :
Page : 156 pages
File Size : 48,57 MB
Release : 1977
Category : Compressibility
ISBN :
Author : Dennis M. Bushnell
Publisher :
Page : 156 pages
File Size : 37,52 MB
Release : 1977
Category : Turbulent boundary layer
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Author : H. James Herring
Publisher :
Page : 99 pages
File Size : 14,29 MB
Release : 1968
Category :
ISBN :
Author : Shimer Zane Pinckney
Publisher :
Page : 68 pages
File Size : 47,24 MB
Release : 1971
Category : Boundary layer
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Author : H. James Herring
Publisher :
Page : 124 pages
File Size : 32,91 MB
Release : 1968
Category : Turbulent boundary layer
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Author : M. C. Altstatt
Publisher :
Page : 46 pages
File Size : 14,5 MB
Release : 1976
Category : Compressibility
ISBN :
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).
Author :
Publisher :
Page : 1282 pages
File Size : 13,8 MB
Release : 1982
Category : Aeronautics
ISBN :
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author : Neal Tetervin
Publisher :
Page : 96 pages
File Size : 49,91 MB
Release : 1967
Category : Enthalpy
ISBN :
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).
Author :
Publisher :
Page : 580 pages
File Size : 37,60 MB
Release : 1969
Category : Compressibility
ISBN :
Author : Larry L. Lynes
Publisher :
Page : 146 pages
File Size : 11,38 MB
Release : 1969
Category : Air flow
ISBN :