20913 急激な迎角変化中の三次元翼に作用する非定常流体力(風車・風力・翼流れ,一般講演)

概要

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Unsteady fluid forces acting on a discoid airfoil were investigated by changing an angle of attack impulsively. The relationship between the transient aerodynamic characteristics and the vortex behavior was described with the flow visualization technique during stepwise incidence variation. The impulsive lift deviates far from the static values in the cases of a small angle of attack change (a lower value than a static stall angle) and low rising rate. When the vortex developed at the trailing edge flows away, the dynamic lift significantly increases and the deviation from the static characteristics enlarges. The changes in the transient aerodynamic characteristics are caused by the vortex shedding from the trailing edge of the airfoil.
社団法人日本機械学会の論文
2009-03-05