On the Navier–Stokes Calculation of Separation Bubbles With a New Transition Model

[+] Author and Article Information
W. Sanz

Institute of Thermal Turbomachinery and Machine Dynamics, Graz University of Technology, Graz, Austria

M. F. Platzer

Department of Aeronautics and Astronautics, Naval Postgraduate School, Monterey, CA 93943

J. Turbomach 120(1), 36-42 (Jan 01, 1998) (7 pages) doi:10.1115/1.2841385 History: Received February 01, 1996; Online January 29, 2008


Laminar separation bubbles are commonly observed on turbomachinery blades and therefore require effective methods for their prediction. Therefore, a newly developed transition model by Gostelow et al. (1996) is incorporated into an upwind-biased Navier–Stokes code to simulate laminar—turbulent transition in the boundary layer. A study of the influence of the two adjustable parameters of the model, the transition onset location and the spot generation rate, is conducted and it is found that it can predict laminar separation bubbles, measured on a NACA 0012 airfoil. Additional results are presented for separation bubbles in an annular compressor cascade.

Copyright © 1998 by The American Society of Mechanical Engineers
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