Development of Overset CFD Technology in Unstructured, Compressible Flow Solver for Arbitrary Polyhedral Meshes, LS-FLOW

The overset grid approach provides a very powerful means of handling complex geometries in computational fluid dynamics. This overset grid approach has many advantages for the moving boundary or the rudders problem. Therefore, an overset unstructured grid method was newly developed for an arbitrary polyhedral compressible flow solver, LS-FLOW. We introduced the IBlank for visualization and post-processing. In order to test the validity of the suggested methods, a numerical simulation was carried out on the NACA0012 airfoil, and our results are compared with experimental data and other CFD results. Furthermore, in order to evaluate the validity of this method, we also simulated the flow around a reusable sounding rocket under research at JAXA/ISAS. The results of the overset grid method correspond with the results of the single grid method in the NACA0012 airfoil case and the reusable sounding rocket. The good coincidence validates our newly developed overset grid method, and we intend to use LS-FLOW as a design tool.