Abstract:

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.

Key words: adapt ive aerofoil, bi-objective optimization aerofoil, numerical optimization