Investigations of Nonlinear Aeroelasticity Using A Reduced Order Fluid Model Based on POD method

摘要

Investigations of nonlinear aeroelasticity of flexible structures subjected to unsteady transonic flows were carried out using a three-dimensional aeroelasticity reduced-order fluid model which is based on the Proper Orthogonal Decomposition (POD). The number of degrees of freedom was reduced from more than 150000 in the full-order model to 200 unknown variables for the reduced-order model (ROM). The dynamic responses of the aeroelastic system, particularly, the wing Limit Cycle Oscillation (LCO) in the transonic regime was simulated. Numerical simulations on the AGARD 445.6 wing show good agreement between the ROM and the original full-order fluid model.