Coupled aerodynamic/structural optimization of a subsonic transport wing using a surrogate model

A multidisciplinary design optimization (MDO) of a high-subsonic transport aircraft wing of a wing/body combination, is demonstrated, which is based on the static aeroelastic effect. A computational method based on quasi-simultaneous viscous-inviscid coupling is used to determine the transonic flow over the wing/body. The structural analysis is carried out by using finite element method (FEM)-based commercial software ANSYS. The surrogate models used for this demonstration improves the computational efficiency and accuracy. Surrogate models like Response-surface method (RSM), kriging model (KM), and radial basis function network (RBF) are used for this optimization. It was observed that surrogate model can easily determine the response due to their low modeling errors. The aeroelastic effect need to be considered to avoid errors in the design phase.