Dynamically Linearized Euler Time-domain Approach with Shock Impingement for LCO Prediction for an Elastic Panel
The application of a nonlinear aeroelastic model for a flexible panel is expanded to consider the Euler equation as the aerodynamic model. This study presents the method to compute the generalized aerodynamic force from a CFD simulation and compares the results previously obtained using Full Potential Flow Aerodynamics and the Linear Piston Theory. The flutter onset critical condition is computed based on the Limit Cycle Oscillation amplitudes, for different supersonic Mach numbers. Additionally, the shock wave effect is considered in the CFD simulation and is implemented in the aeroelastic model via the generalized aerodynamic force obtained by the new approach. Conclusions are made based on the use and application of this more complete aerodynamic theory, particularly for cases with shock-impingement and near transonic Mach numbers.
