An Explicit Scheme for the Calculation of Three-Dimensional Turbulent Boundary Layers

[+] Author and Article Information
J. F. Nash

Aerospace Sciences Laboratory, Lockheed Georgia Research Laboratory, Marietta, Ga.

J. Basic Eng 94(1), 131-138 (Mar 01, 1972) (8 pages) doi:10.1115/1.3425340 History: Received February 08, 1971; Online October 27, 2010


An explicit finite-difference scheme is formulated for calculating the development of the incompressible turbulent boundary layer on an infinite yawed cylinder. The governing partial differential equations are similar to those used by the author in a previous paper [1], and the empirical content is the same. In their general form the difference equations define a two-step scheme containing two disposable parameters, and numerical experiments have been conducted to determine the stability boundaries, and the boundaries of acceptable numerical precision, in terms of these parameters. By a particular choice of one of the parameters the system reduces to a one-step, staggered-mesh scheme, and it is in this form that the method finally emerges. With 15 collocation points through the boundary layer the method has a typical precision of 2 percent, and with 20 points, 0.5 percent.

Copyright © 1972 by ASME
Your Session has timed out. Please sign back in to continue.





Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In