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首页> 外文期刊>The Aeronautical Journal >A wind-tunnel based study of helicopter tail rotor blade vortex interaction
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A wind-tunnel based study of helicopter tail rotor blade vortex interaction

机译：基于风洞的直升机尾桨叶片涡流相互作用研究

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The interaction of a helicopter tail rotor blade with the tip vortex system from the main rotor is a significant source of noise and, in some flight states, can produce marked reductions in control effectiveness. This paper describes a series of wind-tunnel tests to simulate tail rotor blade vortex interaction with a view to providing data for the development and validation of numerical simulations of the phenomenon. In the experiments, which were carried out in the Argyll wind-tunnel of Glasgow University, a single-bladed rotor located in the tunnel's contraction was used to generate the tip vortex which travelled downstream into the working section where it interacted with a model tail rotor. The tail rotor was instrumented with miniature pressure transducers that measured the aerodynamic response during the interaction. The results suggest that the rotor blade vortex interaction is similar in form to that measured at much higher spatial resolution on a fixed, non-rotating blade. The combination of the two datasets, therefore, provides a valuable resource for the development and validation of predictive schemes.
机译：直升机尾桨叶片与主旋翼的尖端涡旋系统之间的相互作用是一个重要的噪声源，在某些飞行状态下，控制效果可能会大大降低。本文介绍了一系列风洞测试，以模拟尾桨叶片涡流相互作用，以期为开发和验证该现象的数值模拟提供数据。在格拉斯哥大学的阿盖尔风洞中进行的实验中，位于隧道收缩处的单叶片转子用于产生尖端涡流，该尖端涡流向下游行进至工作段，并与模型尾桨相互作用。尾桨装有微型压力传感器，可测量相互作用过程中的空气动力响应。结果表明，转子叶片涡旋相互作用的形式类似于在固定的非旋转叶片上以更高的空间分辨率测得的形式。因此，两个数据集的组合为开发和验证预测方案提供了宝贵的资源。

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