摘要
以FLUENT6.1软件为工具,利用湍流k-ε模型,求解二维稳态可压缩N-S方程,模拟了微喷管内的超音速流动,分析了喷管喉部结构不对称对喷管流场与喷管出口推力的影响。这种喉部结构不对称由于喉部上下顶点在x方向上偏离一定距离所造成。数值计算结果表明,喷管喉部上下顶点在流体流动方向的不对称,将导致喷管内部流体流场不平衡性,诱导喷管内部产生康达效应,使得喷管出口的x方向推力减小,y方向产生了多余的推力。
The FLUENT6.1 software is applied to simulate the supersonic flow in micro convergent-divergent nozzle by using the k-ε model. The simulation is complemented by computing steady two-dimensional Navier-stokes equations. The simulation is employed to study flow fields and thrust force at the exit of thruster from asymmetrical throat. The asymmetry of throat is caused by throat upper vertex deviating some distance from lower vertex in x direction. The simulation results show that the asymmetrical of throat structure causes flow fluid perturbation inside the thruster, induces Coanda effects and decreases thrust force in x direction, bringing about thrust force in y direction.
出处
《广东海洋大学学报》
CAS
2010年第1期81-87,共7页
Journal of Guangdong Ocean University
关键词
数值计算
不对称
推力
微喷管
numerical simulation
asymmetry
thrust force
micro thruster
