Dynamic Stall Simulations on a Pitching Finite Wing
Dynamic Stall Simulations on a Pitching Finite Wing
复制标题
俯仰有限机翼的动态失速模拟
DOI：
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发表时间：
2016
期刊：
影响因子：
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通讯作者：
A. Gardner
中科院分区：
文献类型：
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作者：
K. Kaufmann;C. Merz;A. Gardner
一旦超过静态失速角，动态失速对俯仰翼和翼型的气动影响与静态情况有明显不同。较大的阻力与俯仰力矩峰值相关联
The aerodynamic effects of dynamic stall on pitching wings and airfoils differ significantly from the static case, as soon as the static stall angle is exceeded. The large drag and pitching moment peaks associated with
this phenomenon make it impossible to operate helicopters in flight conditions which trigger dynamic stall over large areas of the rotor blade. To simplify the problem, most of the research on dynamic stall focuses
on two-dimensional pitching airfoils. This has lead to an understanding of the process and mechanism of dynamic stall, but has a limited insight into the three-dimensional nature of dynamic stall. There have been a few experimental and numerical studies on full helicopter configurations. These
revealed the very complex flow field around the rotor blades, but the combination of downwash, blade-wakevortex interactions and the elasticity of the rotor blades leads to a limited comparability. An approach
between these configurations is to use stiff pitching finite wings with defined boundary conditions. In these configurations the blade tip vortex reduces and delays the occurrence of dynamic stall in the surrounding
region leading to a strongly three-dimensional flow, see e.g. Le Pape et al. and Lorber.