关键词: 环流喷管~+;喷管气流;纳维尔-斯托克斯方程;网格生成;流场仿真;数值仿真

Abstract: This paper is about numeric imitation of annular-flow nozzles of rocket motors.Navier-Stokes equations are solved by numerical methods. The numerical scheme is MacCormack timeforward-push scheme. Zero-equation which has more relibility is selected to apply to turbulent model.Because of complex boundary condition of flowfields region-dividing is used in the calculation.Through contrasting a lot of calculation examples, geometric parameters of annular-flow nozzles withhigher efficiency are found. The final results of flowfield calculation is steady. The graph of equalMach numbers, the isobar graph, and the graph of pressure distribution along nozzle wall and thecentric line of nozzle are drawed with computer. The drawing of computing grid and the vectorialdrawing of velocity of annular-flow nozzle are obtained.

Key words: Annular-folw nozzle+;Nozzle flow;Navier-Stokes equation;Grid generation;Flow field simulation;Numerical simulation