三角翼大迎角绕流的数值模拟  

Numerical simulation of a delta wing at high angles of attack

作　　者：康顺[1] 杜永乐 祁明旭 

机构地区：[1]华北电力大学,北京102206 [2]尤迈克(北京)流体工程技术有限公司,北京100081

出　　处：《空气动力学学报》2005年第4期395-401,共7页Acta Aerodynamica Sinica

摘　　要：采用FINETM/HEXA非结构网格流场计算软件包对三角翼飞行器的低速大迎角绕流进行了数值模拟。结果表明,计算值与实验数据符合较好,采用Agglomeration方法能大幅度提高收敛速度,而网格自适应方法用总体不大的网格单元数可较精细地模拟流场。本文还分析了前缘分离涡破裂前后的流动现象和旋涡横截面流线图谱的变化规律。Low speed flows around a delta wing body at high angles of attack were simulated by using the flow solver FINE^TM/HEXA which is based on all-hexahedral unstructured mesh. Simulation results show good agreement with the experimental data. The convergence is greatly accelerated with the method of agglomeration, and 3D mesh adaptation can help to capture the delicate flow features while the mesh cell number remains not very large in global. This paper also presents analysis of the flow features ahead and behind of the leading edge vortex breakdown and the topological features of section streamlines.

关 键 词：三角翼 大迎角 数值模拟 涡 涡破裂 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]