Nonlinear Aeroelastic Model Considering RANS Unsteady Aerodynamics with Dynamically Linearized Time-domain Approach
A nonlinear aeroelastic model for a flexible panel is expanded to consider the effect of the viscous boundary layer using a RANS solver. This study presents the use of a Reduced Order Model (ROM) to compute the generalized aerodynamic force from a CFD simulation and compares the results obtained using the same approach with an inviscid solver and the analytical implementation of Full Potential Flow Aerodynamics. The flutter onset critical condition is obtained based on the Limit Cycle Oscillation amplitudes, for different supersonic Mach numbers. Additionally, the effect of different viscous boundary layer thicknesses is explored. Conclusions are made based on the use and application of this more complete aerodynamic theory, particularly for near transonic Mach numbers.
