摘要
分别采用时均RNG湍流模拟和大涡模拟(LES)方法对某型固体火箭发动机内流场进行了瞬态数值模拟研究,建模过程中针对推进剂燃烧以及燃面边界采用了修正壁面通量的方法,并使用了动网格技术。结果表明:大涡模拟技术可以得到发动机内湍流流场中详细拟序结构,时均湍流模拟对于火箭发动机内流场时均量的模拟仍有较好的工程精度。
The turbulence in a solid rocket motor was simulated with Large Eddy Simulation （LES） and RNG model. The dynamic-mesh technology was adopted. The combustion process of the solid propellant was simulated by using a blowing-well. It was shown that the detail construction of turbulence in rocket can be predicted by LES, and the time-averaged method also can give the result with satisfiable engineering precision.
出处
《航空计算技术》
2005年第4期90-93,共4页
Aeronautical Computing Technique
关键词
固体火箭发动机
湍流
数值模拟
solid rocket motor
turbulence
numerical simulation
