摘要
利用时间推进的方法，通过求解可压缩的、雷诺平均的Ｎ－Ｓ方程，并利用Ｂａｌｄｗｉｎ－Ｌｏｍａｘ两层代数湍流模型和Ｐｒａｎｄｔｌ混合长度模型，数值模拟了飞机和火箭发动机喷管的内流和羽流，获得了喷管内流场和羽流场的参数分布，计算结果与试验结果及国外研究成果一致。网格划分采用了自适应网格技术。
In this paper, flow fields of a nozzle and its plume are computed with Mao Cormark time-dependent method. Baldwin-Lomax turbulence model and Reynolds-averaged Naver-Stokes equations as well as adaptive grid technique are apllied to the computation. Two calculation examples are carried out and the computed parameter distributions agree well with experimental and other computed results.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1995年第5期1-6,共6页
Journal of Propulsion Technology
