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以西北工业大学自行研制的微型扑翼飞行器ASN211为研究对象,利用其简化的二维扑翼及平尾串列翼模型进行了非定常数值模拟,分析了扑翼俯仰运动及沉浮运动对平尾气动性能的影响。在数值模拟模块中,模型的俯仰运动及沉浮运动由动网格技术实现。通过计算流体力学(CFD)软件Fluent对此非定常流场进行数值计算,重点研究了扑翼非定常运动尾流对平尾气动效率的影响。定常状态与非定常时均条件下平尾升力曲线的对比分析表明,扑翼的非定常运动能够增大平尾的失速迎角及最大升力系数,因而使平尾的失速特性得到改善。
Based on the ASN211 miniature flapping-wing vehicle developed by Northwestern Polytechnical University, the simplified two-dimensional flapping-wing and flat-tail tandem wing model was used to simulate the unsteady numerical simulation. The aerodynamic performance of flapping-wing pitch motion and ups and downs was analyzed. Impact. In the numerical simulation module, the pitch motion and the ups and downs of the model are realized by the moving grid technology. The computational fluid dynamics (CFD) software Fluent is used to numerically calculate this unsteady flow field. The effects of flapping wing unsteady wake on the aerodynamic efficiency of horizontal tail are studied emphatically. Contrast analysis of flat-tail lift curves under steady-state and unsteady hour-average conditions shows that unsteady movement of flapping wing can increase the angle of attack and the maximum lift coefficient of horizontal tail, thus improving the stall tail stall characteristics.