CFD-Based Aeroelastic Eigensolver for the Subsonic, Transonic, and Supersonic Regimes

We describe a linearized computational fluid dynamics (CFD) method for computing an arbitrary number of eigensolutions of a given aeroelastic problem. The proposed method is based on the reengineering of a three-way coupled formulation previously developed for the solution in the time domain of nonlinear transient aeroelastic problems. It is applicable in the subsonic, transonic, and supersonic flow regimes, and independently from the frequency or damping level of the target aeroelastic modes. It is based on the computation of the complex eigen-solution of a carefully linearized fluid-structure interaction problem, relies on the inverse orthogonal iteration algorithm, and reutilizes existing unsteady flow solvers. This is a validated method with the flutter analysis of the AGARD Wing 445.6 for which experimental data are available.

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