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.
出处
《弹箭与制导学报》
CSCD
北大核心
2012年第4期161-164,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
侧壁边界层
翼型
气动特性
数值模拟
side wall boundary layer
airfoil
aerodynamic characteristics
numerical simulation
