The dynamic stall process on a pitching NACA 0012 airfoil was investigated by two experimental techniques- particle image velocimetry (PIV) and laser-sheet visualizations-and a numerical code based on the Navier-Stokes equations. The freestream velocity was 28 m/s, leading to a Reynolds number (based on airfoil chord) of 3.73xl0~5. The airfoil motion was a sinusoidal function between 5 and 25 deg of incidence, with a frequency of 6.67 Hz corresponding to a reduced frequency (based on airfoil half-chord) of 0.15. The out-of-plane component of the vorticity could be derived from the PIV velocity fields.
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机译:通过两种实验技术-粒子图像测速(PIV)和激光薄片可视化-以及基于Navier-Stokes方程的数字代码,研究了俯仰NACA 0012机翼上的动态失速过程。自由流速度为28 m / s,导致雷诺数(基于翼型弦)为3.73x10〜5。机翼运动是入射角在5到25度之间的正弦函数,其频率为6.67 Hz,对应于降低的频率(基于机翼半弦)为0.15。涡度的平面外分量可以从PIV速度场得出。
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