Numerical Simulation of Aerospace Applications Using Overset Mesh

Overset method is applied for aerospace applications to demonstrate its benefit over traditional dynamic mesh approach. Present study compares inverse distance and least square methods for overset boundary interpolation and shows the accuracy of higher order interpolation methods. An overset mesh consists of a set of overlapping component meshes, which allows complex geometries to mesh with lesser effort. Interpolation methods are enforced at internal boundaries to ensure a continuous solution in overlapping component zones. Finite volume method (FVM) with pressure based coupled solver is used to solve Reynolds Averaged Navier Stokes (RANS) equations. The first case study involves flow over an airfoil (NLF-0414) using static overset mesh where pressure coefficient along the airfoil surface is validated with experimental data. The second case is vortex shedding flow past a cylinder and formation of transient vortices are compared as a function of Strouhal Number (St). In the third case, forced oscillation of a supercritical wing is carried out using moving overset mesh and frequency response functions (FRF) of pressure magnitude are compared with experiment.