摘要
以FLUENT6.1为工具,利用数值计算求解二维稳态可压缩N-S方程,模拟了喉部有无圆弧过渡以及不同的喉部曲率半径对扩张比为5.4的收缩-扩张微喷管x方向质量流速和总压力影响,进而研究了对微喷管的流量系数和推力效率影响.数值计算结果表明:喉部有无圆弧过渡以及不同的喉部曲率半径,将会影响微喷管出口处x方向的质量流速和总压力分布,随着微喷管喉部特征雷诺数的增大,相对应微喷管最大流量和推力的微喷管喉部曲率半径也相应增加.
The FLUENT6.1 software was applied to simulate the supersonic flow in micro convergent-divergent nozzle with 5.4 expansion ratios.The simulation was complemented by computing steady two-dimensional Navier-Stokes equations to study the effect of mass x velocity and total pressure from throat,which has arc or not and different throat arc radius.Also,the fluent mass and thrust force effects were studied.It is observed by the study that x orientation mass velocity of thrust exit and thrust force are effected by...
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第5期1048-1054,共7页
Journal of Aerospace Power
基金
国家自然科学基金资助(50776089)
关键词
数值计算
微喷管
推力
质量流速
numerical simulation
micro nozzle
thrust force
mass velocity
