Immersed Boundary Method for High Reynolds Number Compressible Flows Around an Aircraft Configuration

Abstract

This study focuses on the immersed boundary method (IBM) for high Reynolds number compressible flow. Using the hierarchical Cartesian grid makes it difficult to resolve the thin boundary layer of high Reynolds number flow around an object because the grid is refined equally in every direction. To alleviate the requirement for the grid size of the wall, the development of a wall boundary condition using a turbulent wall function is necessary. The IBM development is based on a hierarchical Cartesian grid generator and compressible flow solver called the University of Tokyo Cartesian-grid-based automatic flow solver (UTCart). The flow solver is validated through subsonic flow over a 2D bump. The skin friction distribution is reproduced accurately by the proposed IBM. A flow around NASA common research model is solved. A flux-based method is developed based on the balance of the numerical fluxes and used for the evaluation of the aerodynamic forces. The results exhibit favorable agreement with the existing experimental data and numerical results from the body-fitted grid.