非共面近距耦合鸭式布局鸭翼展向脉冲吹气增升特性  

Lift-enhancement of canard-spanwise pulsed blowing of non-coplanar close-coupled canard configuration

作　　者：刘杰[1,2] 刘沛清[2] 曹硕[1,2] 

机构地区：[1]成都飞机设计研究所,成都610041 [2]北京航空航天大学流体力学研究所,北京100191

出　　处：《实验流体力学》2011年第4期37-41,共5页Journal of Experiments in Fluid Mechanics

基　　金：国防预研基金项目(9140A13020307HK0127;9140A13040109HK149)

摘　　要：对40°前缘后掠角的主翼和40°前缘后掠角的鸭翼所构成的近距耦合鸭式布局简化模型进行了风洞测力、测压实验,系统研究了鸭翼展向脉冲吹气的增升效果,给出脉冲吹气频率以及脉冲宽度与布局升力之间的变化关系。测力结果表明,鸭翼展向吹气提高了该布局在大迎角时的升力,延迟了失速。测压结果表明,鸭翼展向脉冲吹气改善了中大迎角时主翼翼面流态,增加了翼面吸力峰值,延缓了涡的破裂。这说明利用鸭翼展向脉冲吹气涡控技术,可以直接改善鸭翼流场,继而间接改善主翼流场。A wind-tunnel force and pressure measurement experiment was conducted to investigate the effect of canard-spanwise pulsed blowing on lift-enhancement over a simple close-coupled canard configuration with a 40 deg swept delta wing and a 40 deg swept delta canard. The correlations between the pulse frequencies and width with the lift are presented at different angles of attack. The results of force measurement reveal that the life can be increased at large angles of attack, the critical stall angle can be delay by using canard-spanwise pulsed blowing. The data of pressure measurement show that canardspanwise pulsed blowing improve the flow on the wing at large angles of attack, enhance the suction peak value and delay the breakdown of the wings vortex. So it is possible to directly control the flow of canard and indirectly control the flow of wing by the vortex control technique of canard-spanwise pulsed blowing.

关 键 词：非共面鸭式布局 展向吹气 间接涡控制技术 测力 测压 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]