亚燃/超燃双重燃烧冷态掺混的数值模拟  

NUMERICAL SIMULATION OF COLD MIXING IN THE SUPERSONIC COMBUSTOR OF DUAL COMBUSTION RAMJETS (DCR)

作　　者：索建秦[1] 马继华[1] 金如山[1] 

机构地区：[1]北京航空航天大学

出　　处：《推进技术》1993年第5期8-16,共9页Journal of Propulsion Technology

摘　　要：通过求解完全的二维N-S方程组,对亚燃/超燃双燃烧室冲压发动机超音速燃烧室的冷态掺混粘性层流流动进行数值计算,采用MacCormack两步显式格式分析一股音速来流在两股超音速气流间掺混的流动特征,并用代数法生成计算网格。给出的三组算例与文献[1]的实验结果进行对比,结果令人满意。The flowfield characteristics created by a sonic jet flow between two supersonic streams were investigated theoritically by solving full 2-D N-S equations. A computer program is developed to analyse viscous flowfield of cold mixing of a sonic jet flow with two supersonic streams by using MacCormack explicit scheme. Algebraical method is used in this study to generate computational grids. The agreement of computation with experimental results of reference [1] is rather satisfactory.

关 键 词：超音速燃烧 亚音速燃烧 喷气发动机 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]