A New Model for Boundary Layer Transition Using a Single-Point RANS Approach

[+] Author and Article Information
D. Keith Walters, James H. Leylek

Department of Mechanical Engineering, Clemson University, Clemson, SC 29634

J. Turbomach 126(1), 193-202 (Mar 26, 2004) (10 pages) doi:10.1115/1.1622709 History: Received March 01, 2002; Revised July 01, 2002; Online March 26, 2004
Copyright © 2004 by ASME
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Illustration of wall-limiting concept leading to “splat mechanism” for production of kL
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Profiles of mean velocity (a) and total fluctuation kinetic energy (b) for fully developed turbulent channel flow
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Distribution of turbulent (kT) and nonturbulent (kL) fluctuations in fully developed turbulent channel flow
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Illustration of flat-plate boundary layer test case
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Stanton number versus downstream Reynolds number for each of the three flat plate cases: Tu=0.2% (a), Tu=2.6% (b), and Tu=6.2% (c)
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Profiles of laminar kinetic energy kL in the pre-transitional region of the boundary layer Tu=2.6%. The peak value of kL increases approximately linearly with downstream Reynolds number.
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Profiles of total fluctuation intensity in the pre-transitional region for Tu=2.6% (a) and Tu=6.2% (b). The model predicts fluctuation levels comparable to experimental data documented in Ref. 15.
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Illustration of computational domain for nozzle guide vane test case, indicating high turning and acceleration of passage flow
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Closeup of 2D grid near the leading edge on the suction surface, highlighting the multitopology mesh used to accurately resolve boundary-layer region
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Stanton number versus downstream distance for each of three airfoil cases considered in the present study: Tu=0.6% (a), Tu=10% (b), and Tu=19.5% (c)
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Predicted Stanton number distribution for the three airfoil test cases, using the new model. The figure highlights the influence of freestream turbulence on the simulations.




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