FLUID-STRUCTURE-INTERACTION TECHNIQUE FOR AEROELASTIC STUDIES
A fluid structure interaction technique based on hi-fidelity coupled CSD-CFD solver is developed to study the aeroelastic behavior of aircraft wing in transonic flow regime. Here, the FEM based structural dynamic solver is coupled with the unsteady Navier-Stokes CFD solver in conjunction with mesh morphing algorithm in the time domain. The unsteady N-S CFD solver calculates the aerodynamic forces and moments acting on the wing. The FEM based CSD solver calculates the deformation of the wing using the aerodynamic forces and moments. The mesh morphing technique enables to simulate the flow field over the deformed wing by moving the grid adjacent to the wing surface. The coupled CSD-CFD solver is used to predict the dynamic response of wing in transonic flow regime. The present CFD-CSD approach can predict the transonic behavior of aircraft wing (transonic dip, LCO etc.) with good accuracy. This approach can also be used to study the nonlinear aeroelastic behavior of UAVs with high aspect ratio wings.