Aeroelastic computations in the time domain using unstructured meshes

A strategy for computing aeroelastic solutions is proposed. An implicit LU factorization scheme for solving the time-dependent Euler equations on unstructured triangular meshes is presented and coupled with a typical section aeroelastic wing model. Efficiency is improved by coupling the LU factorization scheme with a GMRES algorithm. In this case the LU scheme plays the role of a preconditioner. The fluid and structural models are simultaneously integrated in time in a fully coupled manner. The response of a structural section in different flow regimes is determined and flutter boundaries are computed. In the transonic regime and beyond the region of linear stability, the section is found to exhibit limit cycle behaviour. (C) 1997 by John Wiley & Sons, Ltd.