翼型分离流动的等离子体控制数值分析方法研究  

Numerical Research and Analysis of Plasma Control of Airfoil Separated Flow

作　　者：王美黎[1] 李栋[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《航空工程进展》2013年第4期481-487,共7页Advances in Aeronautical Science and Engineering

摘　　要：利用等离子体进行流动控制是当前的研究热点之一。本文研究通过数值方法模拟等离子体对流场作用的实现方法,及利用数值模拟方法研究翼型大迎角分离流动的等离子体控制。利用CFD软件Fluent中的自定义函数接口,通过C语言编程在软件中引入DBD等离子体激励模型外加体积力源项,对NACA0015翼型大迎角下的等离子体控制进行数值模拟。验证DBD等离子体激励在抑制流动分离与增升减阻方面的作用。结果表明:流动控制效果与DBD激励器布置位置有直接关系;激励器的数量与激励强度均会影响流动控制作用。The application of plasma actuators for flow control is one of the most popular researches nowadays. By using numerical simulation, two things are mainly studied in this paper： the method of simulating the effect of plasma actuators on flow fields; the plasma control of airfoil separated flow at large angles of attack. A sire plified model for plasma actuators is presented using Fluent User Defined Function（UDF） and the source item of body force is introduced into N-S equations using C language to numerically simulate the plasma control of NACA0015 airfoil at large angles of attack. The results show that DBD plasma actuators can delay flow separation, increase the lift, and decrease the drag of the airfoil. Based on the analysis of numerical results, the location of plasma actuators will directly affect the flow control effect. Moreover, the number and strength of plasma actuators on flow separation is also discussed.

关 键 词：等离子体激励 流动控制 三角区模型 用户自定义函数 流动分离 

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]