摘要
基于固体火箭冲压发动机增程弹丸超音速进气道 ,应用二阶隐式TVD格式对进气道内流场进行了数值模拟 ,得到了不同出口反压条件下 ,超音速进气道流场复杂的波系结构 ,分析了出口反压对进气道启动性能的影响 .结果表明 ,出口反压显著影响着进气道性能 ,反压过高或过低都将导致进气道不启动 。
Based on supersonic inlet of solid rocket r amjet assisted range projectiles, 2-order implicit TVD scheme was used for the numerical simulation of inlet internal flow. Complex wave structures of superson ic inlet under different outflow pressure were achieved by numerical simulation. The influence of outflow pressure on working performance of inlet was also anal yzed. The results show that outflow pressure has great influence on the inlet pe rformance. Relatively high or small outflow pressure all result that the inlet u pstarts. This paper provides theoretical methods for structure design of ramjet assisted range projectiles.
出处
《弹道学报》
CSCD
北大核心
2004年第3期33-38,共6页
Journal of Ballistics
