Numerical simulation research on the transonic aeroelasticity of a high-aspect-ratio wing

Abstract

A numerical simulation based on CDF/CSD methods is conducted to investigate the transonic static aeroelastic issues of large aircraft. The RANS equation and structural statics equations are utilized as governing equations to do coupling iterative calculation. In order to improve the accuracy and efficiency of CFD, multi-block structured grids are employed for parallel computation and the multi-grid method is used to accelerate convergence. Additionally, a dynamic mesh generation technique, based on a radial basis function (RBF) and the transfinite interpolation (TFI) method is adopted to enhance the efficiency and robustness of grid deformation. Moreover, a thin plate spline interpolation technique of three dimensions is utilized to improve the efficiency of data interpolation, coupled with the calculation of structural deformation based on the virtual work principle. The effectiveness of methods used in this paper is validated by a calculation example employing a static aeroelastic model of a wing-body configuration and independently developed software. Based on static aeroelastic analysis of this model in a typical region of transonic Mach number, several suggestions on static aeroelastic correction of large aircraft's aerodynamic coefficients or derivatives can be given.