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首页> 外文期刊>The Aeronautical Journal >Experimental investigation of the flow structures over a 40° swept wing
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Experimental investigation of the flow structures over a 40° swept wing

机译：40°后掠翼流动结构的实验研究

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摘要

Flow over a moderately swept wing is characterised by complex localised flow vortex topologies such as 'closed' separation bubbles or 'open' separation structures. A model of a complex cambered, twisted, tapered wing with 40 degrees leading edge sweep, representative of those designed for manoeuvre at high subsonic Mach numbers, was investigated using the oil-film visualisation, stereo particle image velocimetry and force moment measurements. Wind-tunnel tests were conducted at a range of Reynolds number from 2.1 x 10(5) to 8.4 x 10(5) and at angles of incidence from -1 degrees to 22 degrees. Still images combined with video clips enable flow patterns over the wing model to be interpreted more clearly and accurately. Using successive images extracted from the video of flow visualisation, the movement of the oil pigment has been estimated. The influence of the Reynolds number and incidence angle was discussed through analysing the flow pattern over the wing surface. Additionally, the link between the flow structures present and the wing aerodynamic performance was studied.
机译：在中等程度掠过的机翼上的流动的特征在于复杂的局部流动涡流拓扑，例如“封闭”的分离气泡或“开放”的分离结构。使用油膜可视化，立体粒子图像测速和力矩测量研究了具有40度前掠角的复杂弧形，扭曲，锥形机翼的模型，该模型代表了为在高亚音速马赫数下进行机动而设计的模型。风洞测试的雷诺数范围为2.1 x 10（5）至8.4 x 10（5），入射角为-1度至22度。静止图像与视频剪辑相结合，可使机翼模型上的流动模式得到更清晰，更准确的解释。使用从流动可视化视频中提取的连续图像，可以估算出油性颜料的运动。通过分析机翼表面的流型，讨论了雷诺数和入射角的影响。此外，研究了当前的流动结构与机翼空气动力性能之间的联系。

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