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TECHNICAL PAPERS

Measurements in Separated and Transitional Boundary Layers Under Low-Pressure Turbine Airfoil Conditions

[+] Author and Article Information
Ralph J. Volino

United States Naval Academy, Department of Mechanical Engineering, Annapolis, MD 21402e-mail: volino@usna.edu

Lennart S. Hultgren

National Aeronautics and Space Administration, Glenn Research Center at Lewis Field, Cleveland, OH 44135e-mail: hultgren@grc.nasa.gov

J. Turbomach 123(2), 189-197 (Feb 01, 2000) (9 pages) doi:10.1115/1.1350408 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

Figures

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Schematic of the test section, side view, approximately to scale. Ls=208 mm (wetted length, streamwise length is 206 mm).
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Cp profiles; (a) low TI, (b) high TI
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Free-stream spectra at contraction exit. Re=300.000
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Momentum thickness Reynolds numbers (a): and shape factors (b) for low-TI cases
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Profiles for low-TI, Re=50,000 case: (a) mean velocity, (b) turbulence, (c) intermittency
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Profiles for low-TI, Re=300,000 case: (a) mean velocity, (b) turbulence, (c) intermittency
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Boundary layer u spectra at locations of maximum u, low-TI, Re=300,000 case
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Skin friction coefficient versus Reθ for low-TI cases
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Momentum thickness Reynolds numbers (a); and shape factors (b) for high-TI cases
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Profiles for high-TI, Re=50,000 case: (a) mean velocity, (b) turbulence, (c) intermittency
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Profiles for high-TI, Re=300,000 case: (a) mean velocity (b) turbulence, (c) intermittency
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Boundary layer u spectra at locations of maximum u. high-TI, Re=300,000 case
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Skin friction coefficient versus Reθ for high-TI cases
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Peak intermittency distributions for high-TI cases

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