摘要
飞机在增升装置打开的情况下,襟翼后缘流动分离严重,阻碍升力系数的增加,可以采取主动流动控制的方法控制分离,提高升力系数。本文利用FLUENT 6.3.26软件,针对某多段翼,在襟翼上翼面设置吹吸气孔,分别进行吹、吸气控制,通过改变流量和孔的位置,进行了襟翼上翼面吹、吸气流动控制对二维多段翼型升力性能影响的数值模拟。计算结果表明:应用吹、吸气技术均可获得更高的升力系数,且能延迟边界层的分离;不同的吹吸气孔流量、位置,对多段翼升力增量有不同程度的影响。
The flow separation will happen on the upper surface of the flap when the aircraft take off and landing,this phenomenon makes the lift coeffi cient decrease.By using the active flow control can control the separation and increase the lift coeff icient.In this paper,the numerical simulations carried on a multi-element airfoil by using the flap blowing and suction control is to study the changes of lift coeffi cient by using Fluent6.3.26 software.The suction hole and the blowing hole is separately set on the flap.We change the mass flux and the location of the hole on the flap,the numerical simulations express： blowing and suction control increase the lift coeffi cient,it also can delay the separation of boundary layer;different mass flux and location change the lift coeffi cient differently.
出处
《飞机设计》
2010年第4期10-15,共6页
Aircraft Design
基金
航空基金支持项目(编号:2008ZA51003)
关键词
吹吸气控制
多段翼
流动分离
增升
suction and blowing control
multi-element air foil
flow separation
highlift
