The aerodynamic performance of a deployable and low-cost unmanned aerial vehicle (UAV) is investigated and improved in present work. The parameters of configuration, such as airfoil and winglet, are determined via an optimising process based on a discrete adjoint method. The optimised target is locked on an increasing lift-to-drag ratio with a limited variation of pitching moments. The separation that will lead to a stall is delayed after optimisation. Up to 128 design variables are used by the optimised solver to give enough flexibility of the geometrical transformation. As much as 20% enhancement of lift-to-drag ratio is gained at the cruise angle-of-attack, that is, a significant improvement in the lift-to-drag ratio adhering to the preferred configuration is obtained with increasing lift and decreasing drag coefficients, essentially entailing an improved aerodynamic performance.

中文翻译：

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低雷诺纸飞机的气动优化伴随方法

在目前的工作中，研究和改进了可部署和低成本无人机 (UAV) 的空气动力学性能。翼型和小翼等构型参数是通过基于离散伴随法的优化过程确定的。优化的目标锁定在增加的升阻比和有限的俯仰力矩变化上。将导致失速的分离在优化后被延迟。优化求解器使用多达 128 个设计变量，以提供足够的几何变换灵活性。在巡航攻角下，升阻比提高了 20%，也就是说，升阻比随着升力的增加和减小而得到了显着的改进。阻力系数，