Aeroelastic Analysis of F-16 and F-18/A Configurations Using Adapted CFD-Based Reduced-Order Models

A fast and robust method for constructing aeroelastic reduced-order models (ROMs) at new Mach numbers and angles of attack from a discrete set of aeroelastic ROMs available at dierent Mach numbers and angles of attack is presented. This method is based on interpolation on a tangent space to a Grassman manifold. Its accuracy is assessed with the parameteric aeroelastic identification of two F-16 and F-18/A configurations in subsonic, transonic, and supersonic air streams. In particular, the aeroelastic frequencies and damping coecients predicted by this new ROM interpolation method are compared to counterpart results obtained from full-order nonlinear aeroelastic simulations, alternative ROM adaptation methods, and flight test data. Good correlations are observed, including in the transonic regime. Concluding remarks about the potential of the proposed ROM interpolation method for assisting the flutter test and store clearance of fighter aircraft are also oered.

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