应用重迭网格技术求解复杂组合体无粘流场  

NUMERICAL SIMULATION OF INVISCID FLOW OVER A COMPLICATED BODY USING AN OVERLAPPING GRID TECHNIQUE

作　　者：杨永健[1] 张鲁民[1] 

机构地区：[1]中国空气动力研究与发展中心

出　　处：《空气动力学学报》1991年第1期51-57,共7页Acta Aerodynamica Sinica

摘　　要：本文数值求解了捆绑火箭这一复杂组合体的无粘干扰流场。该计算利用重迭网格(Overlapping Grid)技术求解了分离系数的Euler方程,获得了复杂组合体相互干扰的重要流场特性。通过与风洞试验的比较,计算结果与实验有较好的一致性。An inviscid complex of interaction flow over a launch vehicle with four strap-ons is calculated using the Split Coefficient Matrix method of Euler equations with overlapping grid technique. In order to capture shocks, the monotonic self-adjusting hybrid scheme is also used for the space marching Euler equations. The present numerical results show that all the significant features of an inviscid supersonic flow over multi-bosies are obtained. Multiple shocks reflection and the pressure oscillation between the core and the strap-on can be obtained by the presented method. At the same Mach number, the more narrow the gap between the strap-on and the core, the stronger the surface pressure variation. As the gap is getting smaller than a certain value, the variation of the surface pressure slows down. If the gap between the strap-on and the core is taken as constant, the times of the pressure peak increase with the decreasing the Mach number, the calculating results have shown good agreement with experiment results in CARDC.

关 键 词：复杂组合体 无粘流场 捆绑火箭 

分 类 号：V411.4[航空宇航科学与技术—航空宇航推进理论与工程]