Numerical Analysis and Experimental Techniques for Static Aeroelastic Divergence of Wing

Aeroelastic divergence analysis of a stable wing structure was performed using a coupled aerodynamic/structural method and validated using wind tunnel tests. To ensure the accuracy of numerical analysis, CFD method was used for aerodynamic force calculation and finite element method was used for structural deformation calculation. The wind tunnel test used a sidewall insertion mechanism for support and measured the static aeroelastic divergence characteristics through strain measurement and high-speed photography. The stable wing model was used as the research object for studying the static aeroelastic divergence characteristics in supersonic state. The results of numerical calculation and wind tunnel test showed that the CFD/CSD coupling method can accurately predict the static aeroelastic divergence boundary. Static aeroelastic divergence presents an explosive form of destruction. The static aeroelastic unstable structure first suffers from elastic loading exceeding the structural strength limit and the damage occurs with the dynamic pressure not reaching the divergence boundary. Accurate prediction of the static aeroelastic divergence boundary of the aircraft is necessary for aircraft structural design.