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本文介绍用叠加网格技术对带捆绑助推器运载火箭多箭体的无粘超音造绕流进行的数值模拟方法。这种方法把有充足叠加区域的独立优化的网格用在芯级和每一个捆绑助推器上。流场参数通过叠加区域从一个网格传送到另一个网格。在每一个网格里,用激波捕获技术积分守恒型的欧拉方程。作为一个为模拟超音速绕流建立叠加网格方案的试验,考虑了带捆绑助推器的芯级在M_∞=2.5,零攻角时的简单情况。本文介绍的数值结果是捆绑助推器上的等压线、压力分布、气动载荷分布和侧力变化值。文中把该结果与试验数据及其它数值结果进行了比较。最后,得到带两个助推器的芯级的结果,并把所得压力系数与试验值进行比较。该数值结果表明,叠加网格稳定并能准确地捕获带捆绑级运载火箭无粘流场的所有重要特性。
In this paper, we introduce the numerical simulation of the non-stick supersonic flow around a multi-arrow rocket launcher rocket equipped with superposition grid technique. This method uses independently optimized grids with ample overlay areas on the core level and on each tie booster. Flow field parameters are transferred from one grid to another through the overlay area. In each grid, use the shock-capture technique to integrate the conserved Euler equations. As an experiment to establish the superposition grid scheme for supersonic flow, a simple case of the core with bundling booster at M_∞ = 2.5 and zero angle of attack was considered. The numerical results presented in this paper are the isobars, pressure distribution, aerodynamic load distribution, and lateral force variations on the bundling booster. The results in this paper are compared with the experimental data and other numerical results. Finally, the result of the core stage with two boosters was obtained and the resulting pressure coefficient was compared with the experimental values. The numerical results show that the superposition grid is stable and can accurately capture all the important properties of the non-stick flow fields of the bundled-stage launch vehicle.