摘要
采用三维N-S控制方程和标准k-ε模型,计算了前掠翼和后掠翼模型的气动特性,比较了各自的优势和不足,并通过流场显示分析了其流动机理。研究结果表明:小迎角下后掠翼的升力系数较高,大迎角下前掠翼的失速性能较好,其根源是展向速度的方向相反。后掠翼过早的翼尖失速是导致失速迎角较小的原因。而前掠翼之所以具有良好的大迎角性能,是由于其机翼根侧缘涡和翼尖前缘涡相互作用,对机翼产生上吸力,带来涡升力并且增强了对机翼表面流动的控制能力。前掠翼的流动机理可为先进飞机布局的设计提供理论依据。
Navier- Stokes control equations and standard turbulence model are employed to numerically simulate the aerodynamic characteristics of forward - swept wing （FSW） and backward - swept wing （BSW）. The superiorities and shortages are compared, and then the flow mechanism is analyzed by streamlines display. The research results show that the lift coefficient of BSW is higher in low angle of attack while the stall characteristics of FSW are better in big angle of attack owing to the opposite direction of the spanwise velocity. The premature wingtip stall induces lower angle of attack while stalling. The reason why FSW has better performances during big angle of attack is the favorable interference produced between vortices of side - strake and wingtip leading edge, which affords great vortex lift and enhances the control ability to the flow on the wing surface. The flow mechanism of the forward - swept wing can provide theoretical references for the design of the advanced aircraft configurations.
出处
《空军工程大学学报（自然科学版）》
CSCD
北大核心
2008年第6期11-15,共5页
Journal of Air Force Engineering University(Natural Science Edition)
基金
国防预研基金资助项目(9140A25010406JB3205)
关键词
前掠翼
后掠翼
流动机理
数值研究
漩涡
forward -swept wing （FSW）
backward -swept wing （BSW）
flow mechanism
numerical research
vortex
