基于正交试验的无人机仿生翼型优化设计

Optimization of UAV Wing Bionic Airfoil Profile Design Based on Orthogonal Experiment

针对无人机机翼翼型设计问题,运用仿生学的方法,从生物原型海鸥翅翼上截取翼型,并对获取的原始翼型进行正交试验优化.结果表明,翼型尾部厚度对气动参数升阻比影响最大,优化后的仿海鸥翼型在中低空无人机飞行环境中的气动参数高于航空常用翼型FX60-126、NACA0015、NASA0417,最大升阻比分别增加了58.70%、36.50%、4.00%.在大攻角条件下,能有效延缓气流分离的发生,在攻角变化时有较强的适用性.

In view of the design of unmanned aerial vehicle（UAV）airfoil profile,using bionic method,the airfoil profile is intercepted from the wing of seagull,which is the biological prototype,and the orthogonal test optimization is done on the obtained original airfoil profile.The results show that,the thickness of the rear of airfoil profile has the greatest impact on the lift-drag ratio of aerodynamic parameters;the aerodynamic parameters of the optimized airfoil in imitation of seagull in low-altitude UAV flight environment are higher than usual aeronautical airfoils,such as FX60-126,NACA0015,and NASA0417;the maximum lift-drag ratio increases by 58.70%,36.50% and4.00%.It can effectively delay the occurrence of flow separation,under conditions of high angle of attack,and has better applicability when the angle of attack changes.