自适应翼型的气动外形优化设计

OPTIMIZATION DESIGN OF ADAPTIVE AIRFOIL′S AERODYNAMIC SHAPE

二维翼型自适应的研究是设计自适应机翼的基础。提出了在不同 Ma数、迎角下 ,用 Powell法优化二维翼型前、后缘襟翼的偏转角 ,以获得比常规翼型在亚声速时升阻比大而在超声速时阻力系数小的自适应翼型的研究方案。并与原始翼型以及气动双目标 (亚声速时 ,大升阻比 ;超声速时 ,小阻力系数 )的优化翼型进行了比较 ,证明了自适应翼型比气动双目标的优化翼型气动效率更高。初步探讨了二维翼型前、后缘襟翼的偏转位置对气动效率的影响。

Researching the adaptation of airfoil lays the foundation for designing adaptive wings. Powell method is used to optimize deflection angles of leading and trailing flaps of an airfoil at various Mach numbers and angles of attack.Thus, an adaptive airfoil is obtained whose lift drag ratio at subsonic speed is larger and drag coefficient at supersonic speed is smaller than the baseline airfoil's. The aerodynamic performance of the adaptive aerofoil is compared with that of original airfoil and bi objective optimization airfoil (large lift drag ratio at subsonic speed and small drag coefficient at supersonic speed). It is shown that aerodynamic efficiency of an adaptive airfoil is higher than that of a bi objective optimization airfoil. The influence of airfoil's leading and trailing flaps' deflection location on aerodynamic efficiency is also discussed primarily.