摘要
固体火箭发动机喷管分离流场是相当复杂的，本研究首先建立了分离流的物理模型，采用ＭａｃＣｏｒ－ｍａｃｋ时问推进格式，并用零方程涡粘模型封闭Ｎａｖｉｅｒ—ｓｔｏｋｅｓ方程，计算了一种特型喷管在地面试车时的分离流场，给出了分离图象和出口面参数，本研究所提供的方法还可用于发动机启动过程中喷管的分离计算。
The physical model of separated now is build up for solid rocket engine nozzle. N-S equations are solved using a tine - dependent MacCormack explicit numerical algorithm. Turbulence closure is accomplished with a composite algebraic model. The sepatated flow of the given nozzle during ground fiting test is calculated to present the separation images and the parameters at the exit plane. The method can also be used to predict the separated flow when the solid rocket motor starts.
出处
《固体火箭技术》
EI
CAS
CSCD
1996年第4期18-23,共6页
Journal of Solid Rocket Technology
关键词
火箭发动机
喷管
湍流燃烧
分离流
Rocket motor nozzle
Turbulence combustion
Separated flow
