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TECHNICAL PAPERS

A Time-Linearized Navier–Stokes Analysis of Stall Flutter

[+] Author and Article Information
William S. Clark, Kenneth C. Hall

Department of Mechanical Engineering and Materials Science, Duke University, Durham, NC 27708

J. Turbomach 122(3), 467-476 (Feb 01, 1999) (10 pages) doi:10.1115/1.1303073 History: Received February 01, 1999
Copyright © 2000 by ASME
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References

Figures

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Identification and location of numerical boundary types in computational domain
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Typical computational grid generated for experimental fan blade (Buffum et al. 23); multiple passages are shown for clarity
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NASA Lewis oscillating cascade facility
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Steady pressure distribution on airfoil sources of Buffum cascade; M=0.2, β1=60 deg,Re=380,000
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Steady Mach contours in blade passages of Buffum cascade; M=0.2, β1=62 deg,Re=380,000
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Unsteady pressure distribution on pitching airfoil surfaces of Buffum cascade; M=0.2, β1=62 deg,Re=380,000,k=1.2,σ=180 deg
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Aerodynamic work per cycle due to pitching motion of airfoils for three reduced frequencies; M=0.2, β1=62 deg,Re=380,000
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Magnitude of pitching moment influence coefficients for three reduced frequencies; M=0.2, β1=62 deg,Re=380,000
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Steady pressure distribution on airfoil surfaces of Buffum cascade; M=0.2, β1=70 deg,Re=380,000
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Steady Mach contours in blade passages of Buffum cascade; M=0.2, β1=69 deg,Re=380,000
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Unsteady pressure distribution on pitching airfoil surfaces of Buffum cascade; M=0.2, β1=69 deg,Re=380,000,k=1.2,σ=180 deg
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Steady and unsteady pressure distribution on airfoil surfaces of Buffum cascade for various grid resolutions; M=0.2, β1=69 deg,Re=380,000,k=1.2,σ=180 deg
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Aerodynamic work pre cycle due to pitching motion of airfoils for three reduced frequencies; M=0.2, β1=69 deg,Re=380,000
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Magnitude of pitching moment influence coefficient for three reduced frequencies; M=0.2, β1=69 deg,Re=380,000

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