具有翼柱型装药和潜入喷管的固体发动机内流场计算

Numerical Study on Internal Flow Field of SRM with Finocyl Grain and Submerged Nozzle

本文对具有翼柱型装药和潜入喷管的团体火箭发动机（SRM）燃烧室后部三维流场及喷管三维跨音速流场进行了数值计算，并研究了喷管潜入比对燃烧室后部流场结构的影响。数值计算中以Beam－Warming提出的隐式近似因式分解（AF）方法为基础，引入二阶隐式和四阶显式人工粘性、当地时间步长、隐式残值光顺、稳定因子、分区算法等技术、求解三维薄层N-S方程，得出了一些可供SRM设计参考的结果，也为SRM燃烧室-喷管三维流动一体化计算打下了基础。

Numerical simulation is carried out for the 3-D aft flow field in combustion chamber of SRM withfinocyl grain and submerged nozzle, and for the 3-D transonic flow in the nozzle. The effects of submergenceratio on the flow structure of aft flow field in SRM are also studied. AF method, combined with dissipations,local time step, residue smoothing,stability factor and decomposition of computational domain, is used to solve3-D thin-layer N-S equations and get fairly stable and adaptable results,which provide useful basis for SRMdesign.