用多重网格方法计算旋翼跨声速无粘流场  

Euler solutions of transonic flow for a helicopter rotor in hover using multigrid method

作　　者：杨爱明[1] 翁培奋[1] 乔志德[2] 

机构地区：[1]上海大学上海市应用数学和力学研究所,上海200072 [2]西北工业大学翼型研究中心,陕西西安710072

出　　处：《空气动力学学报》2004年第3期313-318,共6页Acta Aerodynamica Sinica

基　　金：上海市重点学科建设项目;上海市高等学校青年科学基金.

摘　　要：发展了一种加快悬停旋翼无粘流场计算收敛速度的多重网格方法。由于悬停旋翼流场中存在不可压区域,同时旋翼尾涡系统的发展需要较长的时间,使得旋翼流场的收敛速度远低于固定翼流场,因此研究旋翼流场的多重网格算法具有重要意义。空间离散格式采用了中心有限体积方法,时间推进应用了五步龙格 库塔法。采用3层网格的V循环,对一跨声速悬停旋翼无粘流场进行了数值计算。计算结果表明:尽管多重网格方法对旋翼流场的加速收敛作用不如对固定翼流场的加速收敛效果,但是多重网格方法仍然可以显著地加快旋翼流场收敛。An effective multigrid method has been developed to accelerate the Euler solution of transonic flow for a helicopter rotor in hover. The motives of using multigrid method is as the following: the flow near the hub is incompressible, which can slow down the convergence rate; for the most part, the net flow velocity at and in the plane of the rotor wake itself is comprised of the velocities induced by the wake especially by the tip vortices. So the full development of wake is very important for the convergence of the flow field, but it requires a long time in the numerical simulation. Accordingly, the application of acceleration measure is very useful for the rotor computation. In this Euler solver, we use the cell-centered finite volume method in space and advance the solution in time using five-step Runge-Kutta method. A three-level V cycle multigrid method is implemented in a transonic flow computation. Numerical results show that the multigrid method for rotor flow is less effective than for fixed wings, however it can speed up the rotor flow convergence rate remarkably.

关 键 词：旋翼 固定翼 悬停 多重网格方法 流场 空间离散 龙格-库塔法 收敛速度 多重网格算法 加速收敛 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程] V275.1