Gurney襟翼对大后掠三角翼气动特性影响的实验研究  

EXPERIMENTAL INVESTIGATION OF GURNEY FLAPS ON THE AERODYNAMIC CHARACTERISTICS OF HIGHLY SWEPT-BACK PLANE-DELTA WING

作　　者：展京霞[1] 王晋军[1] 李亚臣[1] 

机构地区：[1]北京航空航天大学流体力学研究所,北京100083

出　　处：《兵工学报》2004年第3期363-367,共5页Acta Armamentarii

摘　　要：本文通过风洞实验研究了Gurney襟翼对 70°大后掠角平板三角翼低速气动特性的影响 (基于三角翼根弦长的实验雷诺数为 3.16× 10 5) .实验结果表明 ,Gurney襟翼对以涡升力为主的平板三角翼仍有明显的增升作用 ;在较大的升力系数下 ,Gurney襟翼使相同升力系数下的阻力系数降低 ,从而使三角翼升阻比增加 ;相对高度为 2 .0 %、2 .5 %的Gurney襟翼带来的升阻比相对增量最突出 ,可达 4 0The effects of Gurney flaps on the aerodynamic characteristics of plane-delta wing with a sweep angle of seventy degrees have been investigated through wind-tunnel experiment at a chord Reynolds number of 3.16×10 5. The experimental results indicate that Gurney flap can apparently increase the lift coefficient as well as the drag coefficient of the plane-delta wing, making the lift-drag ratio increase when the lift coefficient is large enough. Gurney flaps with dimensionless height of 2 0 and 2 5% increase the lift-drag ratio of the delta wing much more than others tested in the experiment. Increments up to 40 percent can be attained in comparison with the lift-drag ratio of delta wings without the Gurney flap.

关 键 词：风洞实验 流体力学 三角翼 升力系数 升阻比 GURNEY襟翼 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程] V211.74