Reduced-order modeling of an elastic panel in transonic flow

Reduced-order modeling is applied to a transonic aeroelastic panel that experiences oscillatory motions of a normal shock. Two-dimensional, transonic inviscid flow over an elastic panel produces transonic limit-cycle oscillations over a range of panel parameters. Proper orthogonal decomposition, in concert with domain decomposition, is shown to produce an accurate reduced-order model for the coupled aeroelastic system. Panel flutter in the transonic regime results in a large streamwise movement of a transonic normal shock across the panel surface. The accuracy and order reduction of the reduced-order model is quantified. In addition, the computational savings for this implementation is documented, and the robustness of the reduced-order model to changes in a panel parameter is explored.