后掠机翼欧拉方程数值模拟

Numerical Simulation of the Flows Past Swept Wings Using Euler Equations

本文对后掠机翼用保角转绘加剪切变换生成C-H型网格,并在这类网格拓扑上,用Jameson的三维欧拉方程有限体积法,四步Runge-Kutta时间推进格式,研制出可供分析三维后掠机翼亚、跨、超声速绕流的计算程序。本方法的特色是改进了机翼表面网格点的分布,使机翼后缘与网格线一致。在数值计算中,通过附面层位移厚度计算,引入了附面层粘性修正,改善了计算结果。

In this paper,a computing wing grid of C-H type is generated by means of an improved square root transformation with shearing. For this type of grid,a computer program has been developed for analyzing the subsonic,transonic and supersonic flows over lifting,swept wings by using Jameson's finite volume method for 3-D Euler equations. The resulting difference equations are solved with explicit four-stage Runge-Kutta scheme and implicit residual smoothing for acceleration of the convergence. The method presented has the feature that the trailing wing edge is aligned with the grid line through modification of the distribution of the mesh points on the wing surface.Besides,boundary layer correction has been introduced in numerical calculation through accounting for the displacement effect, so that the computational results presented are further improved.