摘要
对于空气的流动控制问题,由于飞机在飞行中阻力较大,采用表面放电低温等离子体是较为有效的控制方法。采用格子玻尔兹曼模型对连续放置的两组等离子体发生器对边界层流动控制进行数值仿真。得到了壁面附近空气的速度分布。将等离子体发生器布置于NACA0015翼型表面,通过耦合计算得到的驱动速度,得到了等离子体作用前后翼型表面的流场分布以及升力系数、阻力系数曲线。数值仿真结果与实验结果较为吻合,等离子体可以有效的对翼型表面边界层进行控制,增加升力,降低阻力。
Surface discharge low temperature plasma is an effect method for air flow control.Lattice Boltzmann method was employed to simulate boundary layer flow control by means of two plasma actuators.The velocity field of the air near the boundary was obtained.Plasma actuators were placed on the surface of NACA0015 airfoil.By means of coupling with drive velocity,the flow field,lift coefficient and drag coefficient were obtained in having both plasma situation and no plasma situation.The simulation results agree with the experiment results.The low temperature plasma can control the airfoil boundary layer effectively,increase lift force,and decrease drag force.
出处
《计算机仿真》
CSCD
北大核心
2013年第9期101-104,共4页
Computer Simulation
基金
国家863计划(2012AA8091201)
