Investigation of three-dimensional dynamic stall on an airfoil using fast-response pressure-sensitive paint
Investigation of three-dimensional dynamic stall on an airfoil using fast-response pressure-sensitive paint
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DOI：
10.1007/s00348-014-1807-4
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发表时间：
2014-05
影响因子：
2.4
通讯作者：
A. Gardner;Christian Klein;Werner Sachs;U. Henne;Holger Mai;K. Richter
中科院分区：
文献类型：
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作者：
A. Gardner;Christian Klein;Werner Sachs;U. Henne;Holger Mai;K. Richter
使用高速压敏涂料 (PSP) 和压力测量在 0.3 和 0.5 马赫的速度下研究风洞中 OA209 俯仰翼型的动态失速。在 0.3 马赫时，观察到动态失速涡流在机翼中线处比在风洞壁处传播得更快，从而形成“弓形”涡流形状。在 0.5 马赫时，观察到激波引起的失速，激波脚下最初分离，随后分离区域上游、下游和沿翼型宽度扩展。在 0.5 马赫时没有观察到动态失速涡流。通过吹气进行流量控制的研究表明，对于复杂的三维流动，PSP 相对于压力传感器的潜在优势。
Dynamic stall on a pitching OA209 airfoil in a wind tunnel is investigated at Mach 0.3 and 0.5 using high-speed pressure-sensitive paint (PSP) and pressure measurements. At Mach 0.3, the dynamic stall vortex was observed to propagate faster at the airfoil midline than at the wind-tunnel wall, resulting in a “bowed” vortex shape. At Mach 0.5, shock-induced stall was observed, with initial separation under the shock foot and subsequent expansion of the separated region upstream, downstream and along the breadth of the airfoil. No dynamic stall vortex could be observed at Mach 0.5. The investigation of flow control by blowing showed the potential advantages of PSP over pressure transducers for a complex three-dimensional flow.