スモークワイヤ法による振動翼のダイナミックストール現象の研究

第一報 平均迎角の影響

抄録

In the present study experimental efforts have been conducted in order to reveal the detailed flow structure of the dynamic stall in low speed flows. In the present experiments, a low speed wind tunnel, whose diameter is 2m, is used. A special device for oscillating the airfoil in pitch sinusoidally is developed by using a special mechanical link system. The flow fields are visualized by smoke-wire method and smoke lines (streak line) are recorded with a conventional camera and a video camera. The mean angle of attack of the airfoil is changed variously and the effect of mean angle of attack on the characteristics of the dynamic stall are investigated carefully. The results show that the dynamic stall characteristics in low speed flow are significantly influenced by the mean angle of attack.