带侧向喷流的导弹非定常流场模拟  

Numerical simulation on nonsteady flow-field around missile with lateral jet

作　　者：孙得川[1] 贾晓洪[2] 李有年[2] 汪亮[1] 

机构地区：[1]西北工业大学航天学院,西安710072 [2]洛阳光电技术发展中心,洛阳471009

出　　处：《固体火箭技术》2006年第1期25-27,共3页Journal of Solid Rocket Technology

基　　金：中国博士后科学基金项目(中博字;<2003>03号);航空科学基金项目(03D12004)

摘　　要：采用3阶WENO方法计算了大气层内带有侧向喷流的超音速导弹非定常绕流流场。计算显示了在6km高度、Ma=2的条件下喷流放大因子小于1。在最初的1ms内，喷流放大因子急剧变化，形成一个大于1的峰值，在随后的3～4ms内流场趋于稳定。喷流引起的压心变化在前2ms相对质心前移，随后又向后移动到接近质心的位置并趋于稳定。由压强分布得到，喷流启动4～5ms后，流场基本稳定。The nonsteady flow-field around supersonic missile with lateral jet was calculated by means of a third-order Weighted ENO scheme. The calculation results show that amplification factor is less than 1 under h = 6 km,Ma = 2 condition. Within the first 1 ms, amplification factor changes rapidly to form a peak value more than 1 ; within the following 3～4 ms,inner flow-field tends to be steady. Relatively to mass center,pressure center moves forward in the first 2 ms, then moves backward and tends to be steady meat mass center. The pressure distribution indicates that the flow-field is nearly steady after 4～5 ms.

关 键 词：喷流 导弹 非定常流场 WENO方法 放大因子 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]