旋翼表面非定常压力脉动计算的三维自由尾迹非定常面元法

Prediction of Rotor Unsteady Surface Pressure from 3-D Free Wake Unsteady Panel Method

利用最新发展的高分辨率三维自由尾迹非定常面元方法计算多叶片直升机旋翼的三线非定常气动力，将风洞实验数据与旋翼在悬停和出现严重桨润干扰的低速前飞下滑状态下的计算结果进行了比较。在悬停时，还与欧拉方法的结果进行了比较。本方法与欧拉方法的结果以及风洞实验结果都吻合很好。

Newly dcveloped high resolution 3-D panel method has been used to predicte the unsteady aerodynamics of multiblade helicopter rotors. The wind tunnel test rcsults have heen compared with prediction of in hover and in low speed descent where severc BVI is known to occur. In hovering comparion has also been made with Euler method.Good agreement of the prediction with Euler and wind tunnel test results has been obtained.