Simple Methods for Determining the Virtual Origin of Turbulent Boundary Layers in Hypersonic Flow on Sharp-Edged Flat Plates

[+] Author and Article Information
E. J. Hopkins

NASA Ames Research Center, Moffett Field, Calif.

J. Appl. Mech 41(3), 551-553 (Sep 01, 1974) (3 pages) doi:10.1115/1.3423346 History: Received August 01, 1973; Revised March 01, 1974; Online July 12, 2010


For hypersonic Mach numbers up to about 8, the virtual origin for turbulent skin-friction calculations is shown to be close to the beginning of boundary-layer transition. A simple relationship between the beginning and end of boundary-layer transition is presented.

Copyright © 1974 by ASME
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