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TECHNICAL PAPERS

Modification of the NACA 632-415 Leading Edge for Better Aerodynamic Performance

[+] Author and Article Information
Christian Bak, Peter Fuglsang

Wind Energy Department, Risø National Laboratory, P.O. Box 49, DK-4000 Roskilde, Denmark

J. Sol. Energy Eng 124(4), 327-334 (Nov 08, 2002) (8 pages) doi:10.1115/1.1506324 History: Received June 01, 2001; Revised May 01, 2002; Online November 08, 2002
Copyright © 2002 by ASME
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References

Figures

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Time series of cl,cd, and flow speed for the NACA 632-215 airfoil for fixed α=15 deg
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Design variables form a Bezier-curve that represents the leading edge shape, which is transformed onto the original airfoil
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Analysis method to find the critical distance between the natural transition point and the critical transition point to cause leading edge separation
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The natural transition point and the critical transition point to cause leading edge separation for different angles of attack for the NACA 632-415 airfoil (EllipSys2D), Re=3.0×106
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The NACA 632-415 airfoil and the modified airfoil
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Airfoil cl and cd for NACA 632-415 and the modified airfoil (EllipSys2D) compared with measurements of NACA 632-41519, Re=3.0×106
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Airfoil Cp at the leading edge for angles of attack, 6, 10, and 16 deg for NACA 632-415 and the modified airfoil (EllipSys2D), Re=3.0×106
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The natural transition point, xtr,nat, at the suction side for different angles of attack of the NACA 632-415 airfoil compared with the modified airfoil (EllipSys2D), Re=3.0×106
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The natural transition point and the critical transition point to cause leading edge separation for different angles of attack for the modified airfoil, Re=3.0×106
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Measured cl versus cd and cl versus α for the NACA 632-415 for Re=3.0×106 and Re=1.6×106 and the modified airfoil for Re=1.6×106
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Measured cl versus cd and cl versus α for the NACA 632-415 and the modified airfoil with zigzag tape mounted from the leading edge towards the pressure side for Re=1.6×106
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Measured cl versus cd and cl versus α for NACA 632-415 and the modified airfoil with zigzag tape mounted from the leading edge towards the suction side for Re=1.6×106
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Standard deviation for cd versus α for the NACA 632-415 and the modified airfoil with smooth surfaces, Re=1.6×106
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Time series of cd for the NACA 632-415 airfoil at α=20.7 deg, Re=1.6×106
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Time series of cd for the modified NACA 632-415 airfoil at α=20.6 deg, Re=1.6×106

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