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基于NS方程数值模拟方法,研究了‘W’型无尾布局的流动机理。与参照前掠翼布局相比,‘W’布局优越的气动性能来源于其流动形态的变化:小迎角时,翼身融合升力体设计,使机体表面流动更为通畅,升力增加,机体部件干扰减小,部分补偿了因机身加宽,浸润面积增大带来的摩擦阻力,使总阻力没有明显增加。α≥6°,‘W’布局具有新的流动结构,机翼上表面流动由侧缘涡和前缘涡及其诱导的二次涡所控制,侧缘涡与前缘涡之间产生有利干扰,增强了对机翼表面流动的控制能力,不仅带来涡升力,而且有效控制了前掠翼根部流动分离,是其具有优越纵向气动性能的物理原因。‘W’布局新的流动结构为其横侧气动性能改善奠定了基础,为进一步完善布局设计提供了理论依据。
Based on the numerical simulation of NS equations, the flow mechanism of ’W’ tailless layout is studied. Compared with the reference forward swept wing layout, the ’W’ layout superior aerodynamic performance comes from its flow pattern changes: a small angle of attack, the fuselage fusion lift body design, the body surface flow more smooth, increased lift, body parts The interference is reduced, which partially compensates for the frictional resistance brought by the widening of the fuselage and the increase of wetting area, so that the total resistance does not increase obviously. α> 6 °, the ’W’ layout has a new flow structure. The flow on the upper wing surface is controlled by the side vortex and the leading edge vortex and its induced secondary vortex. The edge vortex and the leading edge vortex generate favorable interference , Which enhances the control ability of the wing surface flow, not only brings the vortex force, but also effectively controls the flow separation of the forward swept wing root, which is the physical reason for its superior longitudinal aerodynamic performance. The new flow structure of ’W’ laid the foundation for improving the aerodynamic performance of its lateral side and provided a theoretical basis for further improving the layout design.