摘要
在ＰＩＳＯ算法基础上，发展了一种新的二阶迎风格式以提高计算精度又保证算法的稳定性。新格式应用于液体火箭发动机燃烧流动过程计算，其数值稳定性很好。
Numerical simulation of spray combustion in liquid propellant rocket engine with PISO algorithm was implemented.A second-order upwind scheme developed by the authors was combined with thePISO algorithm to ensure the numerical accuracy.The Navier-Stokes equation in cylindrical coordinates was transferred into general curvilinear coordinate system and discretized by finite-volume method with non-staggered grid.The body-fitted grid generated by TTM method was used in the calculation.A stochastic spray model was employed to determine the droplet initial conditions,and the chemical reaction rate was given by Arrhenius model.The results show that the numerical method and physical models are proper for simulation of spray combustion processes.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1998年第1期81-84,共4页
Journal of Aerospace Power
