摘要
对带振荡的快速上仰翼型的非定常分离流问题进行了计算研究。采用微分形式的动力学方程和积分形式的运动学方程相结合的有效方法,以及可用于有分离流动的Baldwin-Lom ax 湍流模型,精确地模拟大雷诺数大攻角下的复杂流场。依据流场的不同特点,使用分区方法进行计算,保证了计算精度,大大节省了计算时间。文中分析研究了非定常前缘强旋涡的演化过程和气动力的变化。
The problem of unsteady separated flow of rapidly pitching airfoil with oscillating motion is computationally studied. The copulation of kinetic equation in terms of differential form and kinematic equation in terms of integral forms, and Baldwin Lomax turbulent model for separated flows, can be used efficiently in simulating exactly complex flow fields for large Reynolds number and large attack cases. According to different characteristics of the flow field, the zonal numerical method used in the computation can achieve high solution accuracy and save significantly computational time. We′ll analyse evolutional process of unsteady leading edge strong vortex and changes of aerodynamic characteristics, and exploit the effect of different oscillating frequencies and pitching rates on separated flows.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
1999年第6期609-613,共5页
Journal of Nanjing University of Aeronautics & Astronautics
基金
江苏省自然科学基金!(编号:BK97060)
关键词
非定常流动
振荡
分离
上仰翼型
飞机
non steady flow
oscillations
separation
rapidly pitching airfoil
