摘要
针对高超声速乘波飞行器三维绕流流场,在基于LINUX+MPI系统的分布式并行计算平台上,并行求解了三维雷诺平均的N-S方程。并行数值方法采用的是有限体积方法(FVM)、OC-TVD差分格式、B-L代数湍流模型及流场分区的并行方法。计算结果表明,所采用的并行数值模拟方法能够求解包含强激波的流场,激波穿越区域边界时无断层、错位等通量不守恒的现象。并行计算效率高,8个处理机计算时的并行加速比达到了6 8。
Based on the distributed parellel computing platform with the LINUX+MPI parellel environment, a parellel numerical computing method with finite volume method(FVM), OC-TVD scheme, B-L turbulence model and domain decomposition method was developed to solve the 3-D compressible Reynolds-averaged N-S equations. This method was used to simulate the flow field of the hypersonic waverider shape vehicle. The numerical results indicate that the shock across the zone boundary is continuous and the parellel speedup ratio reachs 6.8 when 8 cpu is in using.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2003年第2期5-8,共4页
Journal of National University of Defense Technology
基金
国家863高技术项目资助
关键词
并行计算
高超声速
乘波飞行器
数值仿真
parellel computation
hypersonic
waverider
numerical simulation
