Static Aeroelastic Response Analysis of Aircrafts Based on CFD Pressure Distribution

An analysis method for static aeroelastic response considering the effect of Computational Fluid Dynamics (CFD) aerodynamic pressure distribution was developed in this paper. The aerodynamic pressure and the steady aerodynamic influence coefficient matrix were computed by the high-order panel method and then were corrected according to CFD pressure distribution on the 3D body-surface panel element. The static aeroelastic response was solved by modal method coupling with the structural model. A high-aspect-ratio wing was taken as an example to evaluate the analysis method, and the aerodynamic pressure obtained by CFD method with Euler equation was used for aerodynamics correction on 3D body-surface panel element in this study case. The method was then evaluated by comparing the results with those from the low-order panel method using external aerodynamic pressure and the high-order panel method. The results indicate that the method could provide correct results. The method could be used in the preliminary stage as well as in the detailed stage of aircraft design to provide design guideline of static aeroelastic response analysis.