摘要
为研究前掠角对前掠翼布局气动性能的影响,文中采用N-S方程和标准k-ε模型数值模拟方法,对不同前掠角前掠翼布局的纵向气动性能进行了比较,分析了其流动特性,并总结了前掠角对前掠翼布局气动性能的影响。结果表明:小迎角(α<16°)时,前掠角较小的模型气动效率较高,升力系数和升阻比也较大;大迎角(α>16°)时,随着前掠角的增大,前缘涡和侧缘涡增强,对翼面流动产生有利控制,因而前掠角大的模型升力系数较大。
For study the influence of forward-swept angle on aerodynamic characteristics of forward-swept wing configuration, the longitudinal aerodynamic characteristics of different forward-swept angles were investigated using numerical method based on N-S equation and standard k-ε model, The influence was summarized through analysis of flow mechanism. The result shows when the angel of attack（α〈16°） is low, the aerodynamic effect of the model with small forward,swept angel is higher and the lift coefficient and drag coefficient are larger. When the angel of attack （α〉 16°） is high, with the forward-swept angle getting larger, the vortices produced by side-strake and leading edge become strong, and favorable control on wing surface flow is realized, so the lift coefficients of the model with large forward-swept angel are lager, and the lift-drag rate has no obviously change.
出处
《弹箭与制导学报》
CSCD
北大核心
2009年第4期179-181,272,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
预研基金(9140A25010406JB3205)资助
关键词
前掠翼
旋涡
流动机理
forward-swept wing
vortex
flow mechanism
