Large Deformation Correction for Linearized Time-domain Unsteady Aerodynamics for a Cantilevered Plate

The dynamically linearized time-domain approach (DLTA) reduced order model (ROM) is expanded to include large deformation effects into the aeroelastic solution of cantilevered structures. This correction is used to compute the generalized aerodynamic force from an inviscid CFD simulation and to compare the results with those previously obtained using the first and third-order linear piston theory. The flutter onset critical condition is computed as well as the limit cycle oscillation amplitudes for a range of supersonic and near-transonic Mach numbers. Results show that the DLTA with the large deformation correction can successfully reproduce the piston theory results for Mach number 2.0. For lower values of Mach number, and in post-flutter conditions, the ROM can reconstruct the aerodynamic load beyond the limitations of the piston theory, providing additional insight into the challenges of large LCO response for a cantilevered plate.