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本文用Jameson的三维欧拉方程有限体积法、四步Runge-Kutta时间推进格式,计算机身和大后掠细长机翼的三维可压缩绕流。对钝头机身,用C-O型网格;尖头机身与大后掠细长机翼用H-O型网格。本文介绍钝头旋成体、带座舱前机身和三角翼绕流的计算结果,显示流场等值M线分布,计算压强系数分布与实验比较,以及三角翼大迎角分离涡等。由于用了隐式残值光顺等加速收敛措施,有效地减少推进步数,节省机时。
In this paper, we use Jameson’s Eulerian equation finite volume method and the four-step Runge-Kutta time-advance format to calculate the three-dimensional compressible flow around the fuselage and the large swept wing. On the blunt body, with a C-O-grid; pointed body and large swept slender wings with H-O-type grid. In this paper, the calculation results of the blunt body, the fuselage with front cockpit and the delta wing are presented. The equivalent M-line distribution of the flow field, the comparison of the pressure coefficient distribution and the experiment, and the separation vortex at the high angle of attack of the delta wing are shown. As a result of implicit salvage and other smooth convergence acceleration measures to effectively reduce the number of steps to promote saving machine time.