固体发动机喷管内跨音速旋转流动研究

TRANSONIC SWIRLING FLOW IN SRM NOZZLE

对有旋转情况下的喷管内跨音速流动进行了理论分析，建立了流动模型，导出了壅塞截面上的控制方程，并用数值方法对方程求解，较细致地刻画了有旋转情况下壅塞截面上参数分布。初步研究表明旋转能够有效地减小喷管质量流率。

Theortical analysis of transonic swirling flow in the nozzle of Solid Rocket Motor (SRM) has been made.A flow model has been set up.The governing equations of choking area have been derived and solved by numerical method.Then the distribution of the choking area parameters under the condition of swirling is elaborated.It is shown that the swirling makes the nozzle mass flux decrease.