常气压辉光放电等离子体控制翼型失速的数值模拟研究  

Numerical simulation of flow control past a stalled airfoil with OAUGDP

作　　者：毛枚良[1] 邓小刚[1] 陈坚强[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2008年第3期334-338,共5页Acta Aerodynamica Sinica

基　　金：国家创新研究群体科学基金(批准号:10321002);国家自然科学基金(批准号:10372110)

摘　　要：基于Shyy提出的大气压下均匀辉光放电等离子体与空气干扰的物理模型,通过求解电位势方程得到电场分布,得到了作用于流体上的电场力。通过数值求解考虑等离子体作用的流体运动控制方程,以NACA0015翼型低速绕流为对象,研究了常压辉光放电等离子体位置和个数控制翼型绕流分离的影响。位于分离点上游的等离子体能够有效地抑止翼型分离,而在分离区的等离子体对流动影响很弱,同实验结果一致,并给出了等离子体对翼型气动力影响的规律。Based on the model of the interaction between the OAUGDP（one atmosphere uniform glow discharge plasma） and air proposed by Shyy, the electric forces acting on the air as a body force are obtained after the electric field is gotten by solving the electric potential equation. The impact of the OAUGDP under the conditions of the location and the number of the plasma actuators on the flow past a stalled NACA0015 airfoil at low speed is investigated by solving the NS equation. The rule that the plasma located upstream of the separation point can more efficiently damp the stall of flow around the airfoil than the downstream of the separation point agrees with that of the experimental observation, and simultaneously the effect of plasma on the aerodynamics of the airfoil is investigated.

关 键 词：翼型 低速流动控制 等离子体 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]