摘要
对超燃冲压发动机热环境进行了研究和计算.以二维N-S方程和一维瑞利加热规律为基础,建立了超燃冲压发动机内流场的热环境计算模型;用MacCormark预测-校正格式编写了数值计算程序;对飞行马赫数Ma=6和Ma=8两种工况的超燃冲压发动机内部热环境进行了数值模拟,得到了发动机内部流场的温度分布和壁面热流分布;对计算结果进行了分析.结果表明,采用二维无反应流体计算和一维加热规律相结合的方法,在超燃冲压发动机热环境研究中是可行且有效的.
The scramjet thermal environment was studied in this paper. The computational model for the scramjet thermal environment was established based on the two-dimensional N-S equation and one-dimensional Raleigh heating law. The simulation program was developed using MacCormark forecast-calibration scheme. Thermal environment of the scramjet with Mach 6 and Mach 8 was computed,the scramjet internal flow field temperature and wall heat flux distribution were gained. The analysis of the results shows that the combination of 2D no reaction flow field calculation and 1D heating law of the thermal environment research of scramjets are feasible and effective.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第5期823-828,共6页
Journal of Aerospace Power
