平板/锯齿型Gurney襟翼对NACA0012翼型增升实验研究  

Experimental Investigation of Lift Enhancement on a NACA0012 Airfoil Using Plate/Serrated Gurney Flaps

作　　者：李亚臣[1] 王晋军[1] 张攀峰[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：《航空学报》2003年第2期119-123,共5页Acta Aeronautica et Astronautica Sinica

基　　金：国防科技重点实验室基金资助项目(99JS51HK01);高等学校骨干教师基金资助项目

摘　　要：在Ｒｅ为 2 1× 1 0 6情况下进行的ＮＡＣＡ0 0 1 2翼型Ｇｕｒｎｅｙ襟翼增升效应风洞实验研究表明 ,Ｇｕｒｎｅｙ襟翼可使升力有很大提高 , 0 5%平均气动弦长襟翼在ＣＬ>1 0后即可提供较高的升阻比 ,当ＣＬ =1 3 5时 ,2 %平均气动弦长襟翼获得了 3 5%的最大升阻比增量 ;翼型表面压力分布结果显示 ,Ｇｕｒｎｅｙ襟翼增加了上翼面的吸力 ,同时下翼面压力增强 ,因而升力提高 ;尾流速度型显示Ｇｕｒｎｅｙ襟翼导致流经上翼面的流体在其后有明显下偏转 ,这表明翼型有效弯度增大了 ;襟翼上开出锯齿会同时导致升力和阻力下降 ,但升阻比是否会提高则应视其是否更接近最佳高度的有效迎风面积。Ｇｕｒｎｅｙ襟翼的最佳应用场合为中高升力系数情况 (如起飞、降落等 ) ,在中小升力系数情况下不宜使用。An experimental wind tunnel investigation was undertaken to determine the effec ts of Gurney flaps on a NACA0012 airfoil at a chord Reynolds number of 2 1×10 6. In comparison with the clean configuration results, the Gurney flap increas ed the lift significantly. A higher lift to drag ratio was obtained by the 0 5% C flap when the lift coefficient exceeds 1 0, and a maximum increment of lift to drag ratio was obtained by the 2% C flap at a lift coefficient of 1 35. The pressure distribution results showed that the Gurney flap increased the suction of the upper surface and the pressure of the lower surface, and thu s the total lift. The wake velocity profile indicated a significant down turnin g of the stream over the upper surface of the airfoil, and this revealed that th e camber of the airfoil was increased by the Gurney flap. When serrated, Gurney flaps produced less lift and drag than not serrated ones, but the variation of the lift to drag ratio depends on the effective area of the flaps The Gurney flap should be employed at moderate to high lift coefficient conditions such as takeoff and landing, while not advisable at low to moderate lift coeffici ent conditions.

关 键 词：增升 翼型 GURNEY襟翼 风洞实验 

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]