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Aerodynamic Characteristics of the LS(1)-0417MOD Airfoil Model

[+] Author Affiliations
Jolanta M. Janiszewska, Gerald Gregorek, John Lee

Ohio State University, Columbus, OH

Paper No. WIND2003-349, pp. 1-10; 10 pages
doi:10.1115/WIND2003-349
From:
  • ASME 2003 Wind Energy Symposium
  • ASME 2003 Wind Energy Symposium
  • Reno, Nevada, USA, January 6–9, 2003
  • Conference Sponsors: ASME
  • ISBN: 1-56347-594-4
  • Copyright © 2003 by The American Institute of Aeronautics and Astronautics Inc. and the American Society of Mechanical Engineers

abstract

The LS(1)-0417MOD airfoil model was tested in The Ohio State University’s 3×5 wind tunnel both clean and with the application of leading edge grit roughness and with vortex generators. The tests were conducted in both two-dimensional and three-dimensional model configurations and for steady state and unsteady flow conditions. Pressure data were obtained from six spanwise stations. The results showed that the application of the grit roughness reduces the maximum lift coefficients in all configurations. Unsteady maximum lift coefficients were always higher than those for steady state and had, generally, large hysteresis loops. In the case of the unsteady flow however, the hysteresis loops were smaller for the three dimensional (wing) flows. The smallest hysteresis loops were found at the tip spanwise station. The application of the vortex generators at certain chordwise locations reduced the hysteresis loops and increased the maximum lift coefficient, especially in the three dimensional configuration.

Copyright © 2003 by The American Institute of Aeronautics and Astronautics Inc. and the American Society of Mechanical Engineers
Topics: Airfoils

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