多段翼型风洞侧壁边界层的数值模拟  

Numerical Simulation on Side Wall Boundary Layer of Multi-element Airfoil in Wind Tunnel

作　　者：邓小龙[1] 解亚军[1] 张理想[2] 

机构地区：[1]西北工业大学翼型、叶栅空气动力学国家重点实验室,西安710072 [2]中航工业西安飞机工业(集团)有限责任公司,西安710089

出　　处：《弹箭与制导学报》2012年第4期161-164,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中采用CFD数值方法,对相对厚度为17%的GAW-1多段翼型进行了侧壁边界层的数值模拟,并与西工大NF-3低速风洞的实验结果进行了比较。结果表明:对于NF-3翼型测压实验而言,当攻角小于4°时,风洞侧壁边界层对翼型展向的影响可忽略;当攻角大于4°时,风洞侧壁边界层对翼型中间剖面的流场影响必须加以控制和修正;并验证了NF-3风洞侧壁边界层吹除控制系统可以有效控制侧壁边界层的干扰,改善和提高翼型的气动特性。Based on CFD method, the numerical simulation on side wall boundary layer of GAW-1 Multi-element airfoil with relative thick- ness for 17% was investigated, and compared with the results of Northwestern Polytechnical University＇s NF-3 low speed wind tunnel ex- periments. The results show that, in view of NF-3 wing model in wind tunnel pressure experiments, when the attack angle is less than 4°, the effect of wind tunnel side wall boundary layer on the span direction of airfoil can be neglected, when the attack angle is more than 4°, the effect of wind tunnel side wall boundary layer on the intermediate section of the flow field must be controlled and modified. It is verified that the NF-3 wind tunnel side wall boundary layer blowing system can effectively control side wall boundary layer interference and improve aerodynamic characteristic of airfoil.

关 键 词：侧壁边界层 翼型 气动特性 数值模拟 

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]