旋翼桨叶跨音速绕流的全势方程计算方法  

Calculation Method of Transonic Flow over Helicopter Rotor Blades Based on Full Potential Equation

作　　者：赵景根[1] 徐国华[1] 高正[1] 

机构地区：[1]南京航空航天大学飞行器系

出　　处：《南京航空航天大学学报》1999年第3期245-251,共7页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：在随桨叶旋转的坐标系中，用有限差分法求解非守恒格式的全势方程，建立了一个适用于矩形桨尖和后掠桨尖桨叶跨音速流场计算的方法。该方法运用了Ｊａｍｅｓｏｎ的旋转差分技术，并采用等效迎角方法计入旋翼尾迹的影响。作为算例，首先对无升力状态下具有矩形桨尖和后掠桨尖的ＯＮＥＲＡ桨叶进行了计算，取得了与试验数据相吻合的计算结果。然后，对有升力桨叶，也分别就悬停及前飞状态下的桨叶剖面压力分布进行了计算，通过与试验值的对比，进一步验证了该方法的可靠性。A numerical method is established for the calculation of the quasi steady flow around the helicopter rotor with either straight tip blades or swept tip blades. The non conservative full potential equation is soluted by using finite difference methods under the coordinate fixed on the blades. Jameson′s rotating finite difference methods is adopted and the wake effect is considered by introducing an equivalent angle of attack. As examples, the computations are carried out for the non lifting rotors with straight tip and swept tip, as well as lifting rotors under the conditions of hovering and high speed foward flight. The reliability of this method is verified by compared with the computational results and relative experiments.

关 键 词：旋翼桨叶 跨音速流动 势函数法 有限差分法 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]