中高速条件下不同翼尖小翼的数值模拟分析

Numerical simulation analysis of different winglets under medium-high speed conditions

为研究不同翼尖小翼的减阻特性,选取4种翼尖小翼和翼尖延伸作为研究对象,在相同展长翼尖与中高速飞行条件下(Ma=0.6),利用k-ω剪切应力运输(SST,shear stress transfer)两方程模型对5种不同翼尖装置进行数值模拟。研究5种翼尖装置情况下机翼表面的压力特征和翼尖流场,对比分析了不同翼尖的减阻特性,并对诱导阻力变化原理进行了分析。研究结果表明:不同翼尖小翼气流引导方向不同,改变了机翼表面流场,影响了翼尖压力分布;在中高速条件下,相同展长的融合式和斜削式翼尖小翼相比翼尖延伸减阻效果明显,双羽式翼尖小翼能有效分散翼尖涡。

In order to study the drag reduction characteristics of different winglets,four types of winglets and winglet extensions are selected as the research objects.Under the same extended winglet and medium-high speed flight conditions(Ma=0.6),five different winglet devices are numerically simulated using the k-ωSST(shear stress transfer)two-equation model.The pressure characteristics of the wing surface and the winglet flow field of five types of winglet are studied.The drag reduction characteristics of different winglet are compared and analyzed,along with the principle of induced drag changes.Research results show that the airflow guidance direction of different winglets the surface flow field of the wing and affects the winglet pressure distribution;under the conditions of medium-high speeds and with same wing length,the fused and raked winglets have better drag reduction effect,and the double-feathered winglet can effectively disperse the winglet vortex.