The finite element Galerkin Least Squares CFD code was used to compute loads on rotor blades. This load information was then coupled with aeroelastic analysis using DYMORE. The coupling methodology used is shown in flowchart form in the diagram below. Aeroelastic time response of the blade was obtained during dynamic motion. The diagrams below show the time dependent deformation of a typical rotor blade test case at various time steps. This rotor (used by D. L. Sharpe) consists of two blades with NACA0012 sections.
The colors in the following rotor blade figure indicate velocity magnitudes.
