Abstract
Aerodynamic induced aeroelastic response such as limit cycle oscillation is very difficult for system identification based reduced order model to predict, even for the eigen-mode based reduced order model such as POD/ROM. Also ROMs are very sensitive to parameter variation. A SVM based reduced order model was developed for the nonlinear aeroelastic response prediction. The two-DOF aeroelastic system for NACA 64A010 airfoil in transonic flow was demonstrated for the new nonlinear ROM .The simulation results show the capability and accuracy of the SVM based ROM for nonlinear aeroelastic response prediction. The robustness and computational efficiency of the SVM based ROM would provide a promising tool for real time flight simulation with nonlinear aeroelastic effect.
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