Three-Dimensional Transonic Aeroelasticity Using Proper Orthogonal Decomposition-Based Reduced-Order Models

The proper or thogonal decomposition (POD-) based reduced-order modeling technique for modeling unsteady frequency-do main aerodynamics is developed for a large-scale computational model of a n inv iscid ow transonic wing con guration. When the methodology is used, it isshown that a computational uiddynamic modelwith over three-qua rters of a million degrees of freedom can be reduced to a system with just a few dozen degrees offreedom,while still retaining the accuracy of the unsteady aerodynamics of the full system representation. Furthermore,POD vectors generated from unsteady ow solution snap shots based on one set of structural mode shapes can be used for different structural mode shapes so long as solution snapshots at the endpoints of the frequency range of interest are included in the overall snapshot ensemble. Thus, the snapshot computation aspect of the method,which is the most computationally expensive part of the procedure, does not have to be fully repeated as different structural con gurationsare considered.