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Experimental study of the flow behind an oscillating NACA 0012 airfoil using LDV, hot-film and flow visualization techniques in water tunnel has been carried out and compared with the results of linear theory and of the numerical simulations by the discrete vortex method. The measured thrust coefficient obtained by the momentum balance agrees with the linearlized theory and the numerical simulation for a wide range of oscillating condition. The visualized flow patterns are confirmed by those of the results of the discrete vortex method. The visualized trailing edge flow patterns clearly show the formation and the separation of the boundary layer and its interaction with the shed vortices. The existence of an attached vortex to the trailing edge during some part of the oscillation period is found.
社団法人日本流体力学会の論文