论文部分内容阅读
基于介质阻挡放电等离子体的体积力气动激励机理,仿真研究了等离子体增升减阻技术对沿螺旋桨桨径方向均匀分布的10个叶素气动特性的改善效果。采用叶素理论,对比分析了等离子体对螺旋桨整体气动性能的提高效果。主要结论有:桨尖和桨叶根部的叶素容易发生气动分离现象,其中根部叶素处于负攻角的工况中;采用介质阻挡放电等离子体流动控制技术可以完全抑制流动分离不太严重的桨叶中部区域的叶素气动分离,对桨尖处翼型的严重气动分离不能完全抑制但也有改善作用,但对处于负攻角工况的叶素作用不大;等离子体增升减阻技术确实可以提高螺旋桨的气动性能,对本文所研究的情况,螺旋桨的拉力和效率分别提高了28.27%和12.3%。
Based on the bulk force aerodynamic excitation mechanism of Dielectric Barrier Discharge Plasma, the aerodynamic performance improvement of 10 elements uniformly distributed along the propeller radial direction was simulated by plasma enhanced drag reduction technique. The blade element theory is used to compare and analyze the effect of plasma on the overall aerodynamic performance of the propeller. The main conclusions are: the blade tip and the leaf blade at the root prone to aerodynamic separation phenomenon, in which the root of the leaf element in the negative angle of attack conditions; using dielectric barrier discharge plasma flow control technology can completely inhibit the flow separation is less serious The aerodynamic separation of the vasopressin in the middle part of the blade can not completely suppress but also improve the aerodynamic separation of the airfoil at the tip of the blade. However, it does not play a significant role for the vasopressin in the negative angle of attack. The plasma- It can indeed improve the aerodynamic performance of the propeller. For the situation studied in this paper, the pulling force and efficiency of the propeller are respectively increased by 28.27% and 12.3%.