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TECHNICAL PAPERS

Roughness Sensitivity Considerations for Thick Rotor Blade Airfoils

[+] Author and Article Information
R. P. J. O. M. van Rooij, W. A. Timmer

Delft University Wind Energy Research Institute, Faculty of Civil Engineering and Geosciences, Stevinweg 1, 2628CN, Delft, the Netherlands

J. Sol. Energy Eng 125(4), 468-478 (Nov 26, 2003) (11 pages) doi:10.1115/1.1624614 History: Received January 24, 2003; Revised July 12, 2003; Online November 26, 2003
Copyright © 2003 by ASME
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References

Figures

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Wind tunnel and rotating experiment compared with calculated performance (solid line) both at the 30% section
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Pressure distributions measured and calculated for the rotating situation (Re=1.0×106)
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Comparison in the rotating configuration of measurements with calculations at r/R=0.55 segment 8
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Pressure distributions of two selected data points from experiment and calculations at the r/R=0.55 segment 8
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The shape of three approximately 25% thick airfoils
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Comparison in the clean configuration for DU 91-W2-250 measured by Delft
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Comparison for FFA-W3-241 measured by Risø 13
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Comparison for FFA-W3-211 measured by FFA 14
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The shape of the ZZ-tape applied at the Delft measurements (thickness=0.35 mm)
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Performance for 25% thick airfoils in the clean configuration (S814 is 24% thick)
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The airfoil shapes of two 24% thick airfoils
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Performance for two 24% thick airfoils (clean configuration, VELUX tunnel)
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Airfoil performance for three “25%” thick airfoils with simulated roughness
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Measured data for two 24% thick airfoils with transition fixed at upper (x/c=0.05) and lower surface (x/c=0.1)
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The airfoil shapes of three 30% thick airfoils
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(a) Characteristics for three 30% thick airfoils in the clean configuration (FFA data is at Re=1.6e×106). (b) The lift-to-drag ratio and the lift for three 30% thick airfoils in the clean configuration (FFA data is at Re=1.6e×106).
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Characteristics for 30% thick airfoils in the “rough” configuration (DU at Re=2.0×106, FFA at Re=1.6×106 and AH at Re=1.5×106)
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The lift performance two for 30% thick airfoils in the “rough” configuration (AH at Re=1.5×106, NACA at Re=1.6×106)
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The effect of additional transition (at x/c=0.2) on the lower surface of the DU 97-W-300 airfoil
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Measured and calculated lift performance for DU 00-W-350 and DU 00-W-401 at Re=3.0×106 (clean and transition fixed condition, solid line=calculations)
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A sketch of the vortex generators applied at the wind tunnel tests. Dimensions are in mm
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The effect of vortex generators (x/c=0.2) on the performance of the DU 97-W-300 airfoil
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The effect of vortex generators (x/c=0.2) on the performance of the Risø-A1-24 airfoil
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The effect of ZZ-tape (x/c=0.05) on the performance with vortex generators at x/c=0.2
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The effect of ZZ-tape on the airfoil performance with vortex generators
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The influence of the spanwise position for the clean configuration (Re=3.0×106, solid lines=calculations)
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The influence of rotation for the configuration with fixed transition at Re=3.0×106 (solid lines=calculations)
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Calculated difference in 3-D lift between clean and fixed-transition for 2 airfoils at the inboard blade position for Re=3.0×106

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