绕三角翼旋涡流动的数值模拟

Numerical Simulation of Vortex Flows over a Delta Wing

本文通过高清晰度的Ｎ－Ｓ方程数值模拟对绕大后掠三角机翼的旋涡流动结构及旋涡破裂进行了研究，给出了机翼背风面上复杂的旋涡流动结构，绘制了流动横截面上的截面流线。算例的计算采用了隐式近似因子分解格式。通过算例的计算结果结合拓扑分析理论，对亚声速三角翼背风区主涡及二次涡结构的发展、演变规律进行了探讨。

Flow structures and the nature of vortex breakdown over a delta wing with large swept angle are studied by means of a high resolved simulation through Navier Stokes equations solver.The complex flow structures over the leeside of the delta wing are presented in this paper,and the cross section streamlines are sketched.The solver was developed using the AF scheme.The topological structures and the development of the main and secondary vortices of subsonic flows over the leeside of the delta wing are then analyzed.