Numerical analysis of dynamic stall phenomena of an oscillating airfoil by the discrete-vortex approximation
The flow field around an oscillating airfoil under pitching and/or heaving motion was analized using the discrete-vortex approximation. The maximum angle of attack during oscillation was taken to be larger than the static stall one. The process of the formation of the leading edge separation vortex, its succeeding convection along the wing surface and its shedding into the wake was simulated. The dynamic lift stall curve was obtained when the reduced frequency defined with the half chord length was smaller than 0.25. When it was larger than 0.5, the dynamic lift stall did not occur.
KeywordsUnit Circle Wing Surface Moment Coefficient Discrete Vortex NACA Airfoil
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