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TECHNICAL PAPERS

Aerodynamic Analysis of Blunt Trailing Edge Airfoils

[+] Author and Article Information
K. J. Standish, C. P. van Dam

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

J. Sol. Energy Eng 125(4), 479-487 (Nov 26, 2003) (9 pages) doi:10.1115/1.1629103 History: Received February 27, 2003; Revised July 11, 2003; Online November 26, 2003
Copyright © 2003 by ASME
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References

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Figures

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Effect of truncation on the lift characteristics of the symmetric Gö-490 1
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Airfoils with constant t/c=35% and trailing edge-thickness-to-chord-ratio, tTE/c, of 0%, 5%, and 10%
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DU 97-W-300 with different grids: (a) C-grid; (b) Close-up C-grid; (c) O-grid; (d) Close-up O-grid
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Comparison of measured and calculated lift curves for the DU 97-W-300 at Re=3.0×106 and free transition
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Comparison of measured and calculated lift curves for the DU 97-W-300 at Re=3.0×106 and transition fixed at 5% of chord (top and bottom)
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FX 77-W-343 and FX 77-W-400 airfoils
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Comparison of calculated lift curves for the FX 77-W-343 at Re=3.0×106 for free transition and fixed transition (strU=0.04c;strL=0.03c)
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Comparison of calculated lift curves for the FX 77-W-400 at Re=4.0×106 for free transition and fixed transition (strU=0.04c;strL=0.03c)
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Comparison of calculated lift curves for the TR-35 at Re=4.5×106 for free transition and fixed transition at 5% of chord (top and bottom)
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Truncation of the TR-35 airfoil resulting in the TR-35.80 airfoil
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The scaled TR-35.80 airfoil compared to the original TR-35 airfoil
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Comparison of calculated lift curves for the TR-35.80 at Re=4.5×106 for free transition and fixed transition at 5% of chord (top and bottom)
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TR-44 airfoil compared to TR-35
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MSES calculated lift curves for the TR-44 at Re=4.5×106 with free and fixed transition at 5% of chord (top and bottom)
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Time-averaged pressure distributions of the TR-35.80 and TR-44 airfoils at Re=4.5×106,α=8°, free transition
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TR-35-10 airfoil compared to TR-35
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Comparison of calculated lift curves for the TR-35-10 at Re=4.5×106 for free transition and transition fixed at 5% of chord (top and bottom)
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Time-averaged pressure distributions of the TR-35 and TR-35-10 airfoils at Re=4.5×106,α=8°, free transition
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Relative orientation of CQ and CT to CL and CD with respect to the relative wind, VR, and all pertinent angles at a given radial station
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Change in sectional torque-force coefficient due to blunt trailing edge, ΔCQ=CQTR-35-10−CQTR-35,
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Instantaneous pressure field for the TR-35.80 airfoil at α=0°, depicting the shedding vortices and subsequent drop in pressure at the trailing edge

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