Flows in hypersonic intakes involve multiple shock and boundary layers interaction, reflections, expansions, formation of separation bubbles and transition to turbulent flows under high rates of heat transfer. Accurate numerical representation of such flows requires turbulence treatments beyond RANS, shock capturing methods, and high quality computational meshes for both shock representation and flow resolution in boundary layers. The project will build on the existing high-resolution, high performance, code developed at Loughborough University suitable for simulations of high speed/ hypersonic flows and will focus on developing an effective tool customised for high fidelity hypersonic intake simulations. This will involve the development and testing of effective mesh adaption and shock capturing techniques specific to this application. The current code operates on arbitrary polyhedral meshes with additional options for immersed boundaries and a preliminary h-and r- mesh refinements. After testing, the best performing turbulence treatment will be chosen from the existing capabilities of: LES with a dynamic subgrid model, Implicit LES option, or DES.