摘要
利用商业CFD软件,进行了三维、有粘、定常计算,模拟了某液体火箭大面积比喷管地面条件下的分离流动.计算了多个不同入口总压下的工况.其结果预示了该喷管的分离流动在不同入口总压下的激波模态变化,并获得了非对称分离及其造成的侧向载荷的分布情况.计算为进一步相关研究打下了基础.
A three dimensional, viscous and steady numerical simulation about serpen- tine flow was conducted for a high altitude nozzle of a liquid rocket engine on the ground. The results with different inlet pressure were obtained by utilizing FLUENT software. The transformation of shock pattern and the distribution of unsymmetrical separation and side load in the nozzle were primarily predicted by those results. The simulation provides a key basis for further study.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第11期2114-2118,共5页
Journal of Aerospace Power
