基于旋转修正模型的飞机尾流数值模拟研究

Research on Numerical Simulation of Aircraft Wake Based on Rotation Correction Model

针对现有CFD数值模拟对飞机尾流研究过于简化,仅通过矩形机翼半模进行对称不能完整模拟全局流场的问题,论文对典型中型机A330_200全机模型进行网格划分与数值模拟研究。针对进近阶段选择典型迎角,使用添加旋转修正的SST-RC模型模拟全机尾流场结构。结果表明,由于后掠角的存在,尾流实际为四涡系结构,左右对称。外侧涡对由机翼上下表面压力差诱导产生,翼梢小翼在机翼处将翼尖涡分解为两处较小的涡并在翼尖后5m处合并;下侧涡对由机翼后掠角诱导产生,随后与水平尾翼产生的翼尖涡耦合并向后传递,在约一倍翼展处合并为一条涡系。确定了后续应在机翼翼尖外缘处、翼梢小翼转折处、水平尾翼外缘处三处对尾流场结构进行控制。

Aiming at the problem that the existing CFD numerical simulation is too simplistic for the study of aircraft wake,and the global flow field cannot be completely simulated by the rectangular wing half-mode symmetry,this paper conducts meshing and numerical simulation research on the full model of the typical mid-sized aircraft A330_200.The typical angle of attack is select⁃ed for the approach phase,and the SST-RC model with rotation correction is used to simulate the wake field structure of the whole aircraft.The results show that,due to the existence of the sweep angle,the wake is actually a four-vortex structure,symmetrical.The outer vortex pair is induced by the pressure difference between the upper and lower surfaces of the wing.The wingtip winglet decom⁃poses the wingtip vortex into two smaller vortices at the wing and merges 5m behind the wingtip.The lower vortex pair is generated by the rear of the wing.The sweep angle is induced and then coupled with the wingtip vortices generated by the horizontal tail wing and transmitted backwards,and merge into a vortex system at about double the span of the wings.It is determined that the wake field structure should be controlled at three locations which are the outer edge of the wing tip,the turning point of the winglet,and the out⁃er edge of the horizontal tail.