Computational Analysis for Flapping Wing by Coupled CFD and CSD Solutions

초록

For a flapping wing micro air vehicle (FWMAV), flexibility of the wing structure induces a crucial effect on the vehicle performance. This paper presents an accurate computational approach to simulate flapping wings by coupling between CFD and CSD. For the fluid structure interaction (FSI), a finite volume based preconditioned Navier-Stokes solver with a non-linear structural model based on the geometrically exact beam formulation is used. Aeroelastic analysis is performed, and the results are compared with the experimental results. For the realistic flapping wing analysis, by considering their detailed configuration, the finite element analysis, beam and shell, based on a co-rotational (CR) theory is developed in parallel.