The Leishman–Beddoes dynamic stall model is a popular model that has been widely applied in both helicopter and wind turbine aerodynamics. This model has been specially refined and tuned for helicopter applications, where the Mach number is usually above 0.3. However, experimental results and analyses at the University of Glasgow have suggested that the original Leishman–Beddoes model reconstructs the unsteady airloads at low Mach numbers less well than at higher Mach numbers. This is particularly so for stall onset and the return from the fully stalled state. In this paper, a modified dynamic stall model that adapts the Leishman–Beddoes dynamic stall model for lower Mach numbers is proposed. The main modifications include a new stall-onset indication, a new return modeling from stalled state, a revised chordwise force, and dynamic vortex modeling. The comparisons to the Glasgow University dynamic stall database showed that the modified model is capable of giving improved reconstructions of unsteady aerofoil data in low Mach numbers.
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August 2008
Research Papers
A Modified Dynamic Stall Model for Low Mach Numbers
F. N. Coton
F. N. Coton
Professor
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W. Sheng
Research Assistant
R. A. McD. Galbraith
Professor
F. N. Coton
Professor
J. Sol. Energy Eng. Aug 2008, 130(3): 031013 (10 pages)
Published Online: July 3, 2008
Article history
Received:
February 28, 2007
Revised:
October 5, 2007
Published:
July 3, 2008
Citation
Sheng, W., Galbraith, R. A. M., and Coton, F. N. (July 3, 2008). "A Modified Dynamic Stall Model for Low Mach Numbers." ASME. J. Sol. Energy Eng. August 2008; 130(3): 031013. https://doi.org/10.1115/1.2931509
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