三维多段机翼复杂流场的计算和分析  

Calculation and Analysis of the Flow Passing through a Multi-Element Wing

作　　者：吴宗成[1] 朱自强[1] 李津[1] 陈泽民[1] 

机构地区：[1]北京航空航天大学飞行器设计与应用力学系

出　　处：《北京航空航天大学学报》2001年第3期321-324,共4页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：采用中心差分的有限体积方法和分区技术求解了N S(Navier Stokes)方程 ,在分区求解技术中采用了满足通量守恒的内边界耦合条件 .分析讨论了三维襟翼的绕流流场 ,对“剪刀差”处的三维分离进行了探讨 ,初步揭示了绕流的主要特征及对附近物面压强的影响 .同时 。The N-S equation is solved using a finite volume method with central difference scheme and a domain decomposition technique, an internal coupling condition satisfying the conservation of flux is used in the domain decomposition method. The complex flow field passing through a three-dimensional wing with flap is analyzed, the main features of the separated flow field are shown, it is discussed the formation of the flap side-edge vortex and its influence on the aerodynamics characteristic, meanwhile, the flap leading-edge bubble separated flow is also illustrated.

关 键 词：襟翼 分离流动 纳维尔-斯托克斯方程 三维 飞机 机翼 复杂流场 计算 

分 类 号：V214.11[航空宇航科学与技术—航空宇航推进理论与工程] V211.3