中文摘要：

为了研究低雷诺数下微小型飞行器布局的流动机理,在水槽中对展长/根弦长之比为0.5的一系列变弹性和后掠角机翼的绕流结构进行了氢气泡流动显示实验。结果表明,在低雷诺数条件下,流动结构变化规律如下：随着后掠角增大,弹性翼绕流遵循“Ω涡-一对前缘涡-一对前缘涡与双涡-一对前缘涡、双涡与三涡-一对前缘涡与双涡-一对前缘涡”的变化规律,刚性翼绕流的涡结构变化规律与弹性翼相似,但不存在三涡结构。

英文摘要：

To investigate the flow mechanism of micro-air-vehicle＇ s layout, hydrogen bubble visualization on a series of models with different flexibility and sweep angle whose ratio of span to chord length is 0.5 was carried out in water tunnel. As the results shown, the rule of flow structure to obey at low Reynolds number is listed as follows： the flow around flexible wing follows the rule which is ＂Ω vortex-one pair of leading vortexone pair of leading vortex and dual vortex-one pair of leading vortex, dual-vortex and tri-vortex-one pair of leading vortex and dual-vortex-one pair of leading vortex＂ as the sweep angle increases, the flow structures over rigid wing are almost the same as flexible one but without tri-vortex structure.