摘要
本文用试验的方法显示了悬停状态旋翼的尾迹几何形状，并以试验结果为依据对现有的尾迹几何模型进行了修正。最后以两个模型旋翼为例，分别用修正前和修正后的尾迹几何模型计算它们在悬停时的气动特性和桨叶处的诱导速度分布。所得结果表明用修正后的尾迹几何模型来计算悬停状态旋翼的气动特性能有效地改善计算结果的准确性。
The wake geometry feature of helicopter rotor in hovering is visualized by experimental method in this paper and the preceding wake geometry model is updated according to the experimental results. Finally,with the changed and unchanged wake geometry model,two model rotors are taken as an example to calculate the distribution of axial induced ve1ocity of one model rotor blade and aerodynamic characteristics of the another. It is found that the updating wake geometry model makes an effective improvement in the accuracy of calculating the aerodynamic characteristics of helicopter rotor in hovering compared to the preceding wake geometry model.
出处
《空气动力学学报》
CSCD
北大核心
1995年第3期303-308,共6页
Acta Aerodynamica Sinica
