Laminar and Turbulent Incompressible Boundary Layers on Slender Bodies of Revolution in Axial Flow

[+] Author and Article Information
T. Cebeci

Aerodynamics Research Group, McDonnell Douglas Corp., Douglas Aircraft Co., Long Beach, Calif.

J. Basic Eng 92(3), 545-550 (Sep 01, 1970) (6 pages) doi:10.1115/1.3425060 History: Received May 21, 1969; Online October 27, 2010


The boundary-layer equations for both laminar and turbulent incompressible flows over slender bodies of revolution in axial flow are solved by an implicit finite-difference method. The Reynolds shear-stress term is eliminated by means of an eddy-viscosity concept. Velocity profiles and values of local skin-friction coefficient are obtained for various slender circular cylinders in both laminar and turbulent flows. The deviation of the cylinder skin friction from that of a flat plate is studied. The calculated velocity profiles for turbulent flow are compared with those of both Richmond’s and Yasuhara’s experimental data and with Rao’s proposed formulation of the law of the wall in thick, axisymmetric turbulent boundary layers. In both cases excellent agreement is obtained.

Copyright © 1970 by ASME
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