摘要
本文对俯仰振荡和快速上仰翼型的非定常动失速问题进行了计算研究。对绕流流场采用了高效率的分区精确数值模拟的研究方法,保证了计算结果的精度,大大节省了对非定常粘性流动至关重要的计算机时。文中单独划出前缘驻点区,对形成前缘动失速旋涡的前缘附近区域的流场进行精确计算。算例显示了动失速流场的形成、变化过程及其对气动特性的影响,计算结果和实验的比较是满意的。
The problem of the unsteady dynamic stall of airfoils oscillating in pitch and pithed rapidly is studied computationally in this paper. The zonal numerical method, which is used in simulating efficiently and correctly the flowfield surrounding airfoils and achieves high solution accuracy, can save significantly computational time, which is very important for studing the unsteady viscous flow problem. In the present research leading edge stagnation zone is divided separately, and flowfields in the vicinity of the leading edge, on which the leading edge dynamic stall vortex is generated, are computed accurately. Examples give the process of the formation and change of dynamic stall flowfields and effect on the aerodynamic characteristics. Computed results are shown to be in good agreement with availble experiment data.
出处
《空气动力学学报》
CSCD
北大核心
1992年第3期379-384,共6页
Acta Aerodynamica Sinica
基金
航空科学基金
