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This study presents a framework for aeroelastic stability boundary for hypersonic vehicles using CFD and radial basis functions for mesh deformation. The results are presented for two cases: the aeroelastic stability of a two-dimensional typical cross section and a three-dimensional low aspect ratio wing, representative of a control surface of a hypersonic vehicle. Dierent models of the air mixture are considered: calorically

Hypersonic Aeroelastic Stability Boundary Computations Using Radial Basis Functions for Mesh Deformation