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TECHNICAL PAPERS

Measurements in a Turbine Cascade Flow Under Ultra Low Reynolds Number Conditions

[+] Author and Article Information
Kenneth W. Van Treuren

Department of Engineering, Baylor University, Waco, TX 76798-7536

Terrence Simon

Department of Mechanical Engineering, University of Minnesota, Minneapolis, MN 55455

Marc von Koller

Bundesamt fur Wehrtechnik und Beschaffung, Koblenz, Germany

Aaron R. Byerley

Department of Aeronautics, USAF Academy, Colorado Springs, CO 80840

James W. Baughn

Mechanical and Aeronautical Engineering, University of California, Davis, CA 95616

Richard Rivir

Aero Propulsion and Power Directorate, Wright Laboratories, Wright-Patterson AFB, OH 45433

J. Turbomach. 124(1), 100-106 (Feb 01, 2001) (7 pages) doi:10.1115/1.1415736 History: Received February 01, 2001
Copyright © 2002 by ASME
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References

Figures

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Linear cascade facility at the United States Air Force Academy
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Detail of loss coefficient pitot rake
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Vortex generators and template
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Passage flow for ReNASA 28 K and 1 percent FSTI—a sketch showing observations with tuft
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Flow region shown by tufts located at the 40 (top), 70 (middle), and 90 percent (bottom) suction surface length positions as measured from the leading edge; ReNASA ∼28,000; 1 percent FSTI
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Cp plot for ReNASA=28,000, FSTI ∼1 percent; the “earlier data” were taken under similar conditions but several months prior to the current tests
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Loss coefficient for ReNASA=28 K, FSTI ∼1 percent
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Passage flow for ReNASA 24 K and 9 percent FSTI—a sketch showing observations with tuft
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Upper photo shows separated flow region on the pressure surface. Bottom photo shows the unsteady separated flow region near the trailing edge of the blade on the suction surface. ReNASA ∼24,000; FSTI ∼1 percent.
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Cp plot for low ReNASA with FSTI 1 and 9 percent
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Cp plot using hot-wire velocity to normalize Cp
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Loss coefficient ReNASA=24 K
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Cp plot for ReNASA=59 K; FSTI ∼1 percent with vortex generators
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Loss coefficient ReNASA=54 K; FSTI ∼1 percent

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