旋翼三维非定常跨音速绕流的数值模拟  

NUMERICAL SIMULATION OF 3 D UNSTEADY TRANSONIC FLOWS OVER ROTARY WINGS

作　　者：刘秋生[1] 沈孟育[1] 王保国[1] 濮存斌[2] 

机构地区：[1]清华大学工程力学系 [2]北京空气动力研究所

出　　处：《航空学报》1996年第5期582-585,共4页Acta Aeronautica et Astronautica Sinica

摘　　要：利用小扰动位势方程，用有限差分方法求解了旋翼跨音速流场。导出了严格的三维非定常位势方程远场无反射边界条件，并成功地用于数值计算中，缩小了物理求解域的空间尺度。采用了贴体坐标和网格加密技术，以得到合理的非均匀网格分布。应用较少的网格点数成功地计算了无升力情况下旋翼的三维非定常亚、跨音速绕流流场。A numerical method of 3 D unsteady transonic flows about rotary wings is proposed. The small disturbed potential equation is solved by using the finite difference method. The non reflecting boundary conditions in far boundaries are derived and successfully applied in the numerical calculation. They reduce the size of physical solution domain. Body fitted and non uniform meshes are constructed to obtain high accuracy. In this way, 3 D unsteady subsonic and transonic flows for non lifting rotors are calculated with fewer grids, and the numerical results are in good agreement with the experimental data.

关 键 词：旋翼 非定常流 势流 边界条件 

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]