摘要
本文成功地用隐格式求解无喷管发动机一维非定常有加质两相跨音流场 ,为无喷管发动机内弹道的工程计算提供了一个通用的方法。而且 ,这一成果为整个固体火箭发动机领域流场的一体化计算打下了基础。文中给出了两个算例 ,给出了计算与实验结果对比的情况。
A computational model with an implicit numerical integration scheme is successfully applied to computation of the one-dimensional time-dependent two-phase transonic flow field in nozzleless solid propelland rocket motors.In addition,this achievement provides the basis of integrative performance calculation for all kinds of solid rocket motors.We introduce a concept of equivalent ignition channel,which simplified the treatment of headstream boundary conditions.When deducing the expressions of the elements in the coefficient matrix,we get derivatives before we replace the differential with finite difference.This approach not only makes the expressions succinct,but also saves the time of computation.In the inverse operation of the matrix in two-phase flow computation,the characteristics of the matrix are taken into account,and therefore the computation time is further shortened.Two numerical examples are given.Comparison of the calculations with the motor tests shows a good agreement between the calculated and the measured values.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1991年第2期110-114,共5页
Journal of Aerospace Power
关键词
火箭发动机
跨音速流
隐格式法
Aerodynamics
Transonic
Flow Of Fluids
Two Phase
