Unstable aerodynamic performance of a very thick wind turbine airfoil CAS-W1-450
Unstable aerodynamic performance of a very thick wind turbine airfoil CAS-W1-450
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非常厚的风力涡轮机翼型CAS-W1-450的气动性能不稳定
DOI：
10.1016/j.renene.2018.08.086
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发表时间：
2019-03
期刊：
影响因子：
8.7
通讯作者：
Xu Jin
中科院分区：
文献类型：
--
作者：
Zhang Lei;Li Xingxing;Li Shuang;Bai Jingyan;Xu Jin
非常厚的风力机翼型的流动分离总是会影响翼型的动态性能。在Re=1.0×10ˆ6的风洞中研究了45%厚翼型CAS-W1-450的不稳定气动性能。使用涡流发生器（VG）和M型后缘装置（M板）两种气动附件来改变表面状况。然后研究了附件对非稳态分离的影响。结果表明，厚翼型在大攻角时存在严重的三维边界层分离。分叉通常出现在失速状态附近，因为时间平均流量模式无法维持单一状态，并且压力信号明显从一个值跳跃/下降到另一个值。因此，接近失速和其他一些工况下的测试数据分散很大。 VG 和 M 板的测量表明，VG 可以延迟或消除翼型上的失速和分叉，但 M 板对分叉的影响较小，因为下游的扰动对上游流动的影响较小。对于非常大攻角下的流动条件，发现尽管分离在非常大攻角下非常不稳定，但时间平均气动性能变化较小且可重复。
The flow separation of very thick wind turbine airfoils always causes dynamic performance of the airfoils. The unstable aerodynamic performance of the 45% thick airfoil, CAS-W1-450, was studied in a wind tunnel at Re = 1.0 × 10ˆ6. Two types of aerodynamic accessories, i.e., vortex generators (VGs) and M-type trailing-edge device (M-plate) were used to change the surface condition. And then, the effects of the accessories on the unsteady separation were studied. The results show that the thick airfoil has serious three-dimensional boundary-layer separation at large angles of attack. Bifurcation appears typically near stall condition because the time-averaged flow mode cannot maintain a single state and the pressure signals obviously jump/drop from one value to another. As a result, the testing data near stall and at some of other conditions scatters a lot. Measurements of VGs and M-plate show that VGs can delay or eliminate both stall and bifurcation on the airfoil, but M-plate has less effect on the bifurcation because perturbations downstream have less effect on upstream flow. As for flow conditions at very large angles of attack, it is found that the time-averaged aerodynamic performance varies less and is repeatable, although separation is strongly unsteady at very large angles of attack.
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