A Bypass Transition Model for Boundary Layers

[+] Author and Article Information
M. W. Johnson

Department of Mechanical Engineering, Turbomachinery Group, University of Liverpool, Liverpool, United Kingdom

J. Turbomach 116(4), 759-764 (Oct 01, 1994) (6 pages) doi:10.1115/1.2929470 History: Received February 19, 1993; Online June 09, 2008


Experimental data for laminar boundary layers developing below a turbulent free stream show that the fluctuation velocities within the boundary layer increase in amplitude until some critical level is reached, which initiates transition. In the near-wall region, a simple model, containing a single empirical parameter, which depends only on the turbulence level and length scale, is derived to predict the development of the velocity fluctuations in laminar boundary layers with favorable, zero, or adverse pressure gradients. A simple bypass transition model, which considers the streamline distortion in the near-wall region brought about by the velocity fluctuations, suggests that transition will commence when the local turbulence level reaches approximately 23 percent. This value is consistent with experimental findings. This critical local turbulence level is used to derive a bypass transition prediction formula, which compares reasonably with start of transition experimental data for a range of pressure gradients (λ θ = −0.01 to 0.01) and turbulence levels (Tu = 0.2 to 5 percent). Further improvement to the model is proposed through prediction of the boundary layer distortion, which occurs due to Reynolds stresses generated within the boundary layer at high free-stream turbulence levels and also through inclusion of the effect of turbulent length scale as well as turbulence level.

Copyright © 1994 by The American Society of Mechanical Engineers
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