摘要
为快速预估飞行器喷焰流场及其在一定空域内产生的凝结尾迹,为飞行器目标红外辐射研究提供条件,采用一种工程模型对含复燃效应和水汽凝结效应的喷焰流场进行计算分析。模型以燃气射流的一维流动理论、湍流混合以及化学平衡条件为基础建立控制方程,并采用四阶Runge-Kutta方法进行求解计算。模型校验和分析表明,该工程计算方法能够获得喷焰流场射流区的典型参数,并具有较高的计算效率。
To predict exhausted jet flow and contrail in specific altitude from rocket engine efficiently , an engineering method was performed to calculate jet flow including afterburning and contrail effect .Control equations based on one-dimensional flow theory , turbulent mixing and equipment chemistry reaction were solved by the method of fourth-orders Runge-Kutta.Model verification and example prove that typi-cal parameters of exhausted jet flow in the jet flow region could be achieved by this method , which is more computationally efficient .
出处
《弹箭与制导学报》
CSCD
北大核心
2016年第2期83-86,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
空军装备预先研究项目(61901060601)资助
关键词
喷焰流场
凝结尾迹
复燃
工程计算
exhausted jet flow
contrail
afterburning
engineering calculation method
