Static Aeroelastic Research of Supersonic Wing

Abstract

The thin airfoil design and the supersonic flight condition make the aeroelastic deformation have an important effect on the aerodynamic characteristics of the supersonic aircraft. In this paper, a supersonic Unmanned Aerial Vehicle (UAV) wing is taken as the research object, and the static aeroelastic weak coupling calculation method (CFD/CSD) is used to carry out the modification of the aerodynamic coefficient of the wing. The analysis results show that the aeroelastic deformation reduces the lift coefficient, and the pitch moment produces a head-up increment. At the same time, the aerodynamic focus of the wing moves forward, which reduces the static stability margin of the aircraft. The influence of aeroelastic deformation on aerodynamic characteristics increases with increasing Mach number.