Computational aeroelasticity using a pressure-based solver

The fluid-structure interaction problem is studied for two different wing configurations based on moving grid techniques. These configurations demonstrate the interaction between a rigid structure and fluid, as well as the interaction between a flexible structure and fluid. A loosely coupled approach is used to perform the combined fluid and structure computations. The flow solver is based on an unsteady, implicit, three-dimensional, multi-block, pressure-based Navier-Stokes solver. The rigid structural model is based on a linear, time-invariant model derived via classical structural finite elements whereas the flexible structural model is based on a non-linear dynamic membrane model with the material obeying the hyperelastic Mooney's model. A suitable interfacing technique is incorporated to couple and synchronize the flow and structure solver. We present unsteady computations performed on a 45° wing with sweep back as well as a membrane wing typically motivated by micro-air vehicle applications.