A computational aeroelastic model based on the ONERA M6 wing configuration is studied over a range of transonic flight conditions and structural stiffness parameters. A reduced-order modeling (ROM) approach is used, consisting of linear state-space models based on nonlinear CFD results. The structural component of the models is generated by converting a finite-element model to modal form, while the aerodynamic component is generated via Roger's Rational Function Approximation (RFA). It is shown that although the state-space models are linear, they are effective at predicting conditions where the full nonlinear model shows instabilities, including instabilities unique to the transonic regime such as high-altitude flutter and single-degree of freedom flutter.
展开▼
