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This paper provides a validation of an immersed boundary method for computing hypersonic rarefied gas flows. The method is based on the solution of the Navier‐Stokes equation and is validated versus numerical results obtained by the DSMC approach. The Navier‐Stokes solver employs a flexible local grid refinement technique and is implemented on parallel machines using a domain‐decomposition approach. Thanks to the efficient grid generation process, based on the ray‐tracing technique, and the use of the METIS software, it is possible to obtain the partitioned grids to be assigned to each processor with a minimal effort by the user. This allows one to by‐pass the expensive (in terms of time and human resources) classical generation process of a body fitted grid. First‐order slip‐velocity boundary conditions are employed and tested for taking into account rarefied gas effects.

Simulation of hypersonic rarefied flows with the immersed-boundary method