Calculation of a Hypersonic Flow over Bodies of Complex Configuration on Unstructured Tetrahedral Meshes Using the AUSM Scheme

An approach to solving the three-dimensional Navier–Stokes equations on tetrahedral computational meshes on the basis of splitting by physical processes is considered. An algorithm of numerical implementation of the suggested method for solving three dimensional problems of aerothermodynamics of free-configuration hypersonic flying vehicles (HFVs) is elaborated. The finite-volume method is applied to approximate the gasdynamics equations. The fluxes on the boundaries of the computational elements are calculated using the AUSM scheme. A computer code aimed at numerical simulation of the three-dimensional aerothermodynamics of the structural elements and the integral configurations of the HFV on the basis of the Euler and Navier–Stokes equations is developed. The algorithms developed are tested using the benchmark problem of a viscous hypersonic perfect gas flow over a sphere. The results of comparison of the computational data found using the suggested approach on the unstructured different-size meshes with the numerical solutions found on structured grids with application of the computational code NERAT are presented. The computational model of the flow of viscous and inviscid perfect gas developed is applied to investigate the aerothermodynamics of a model of an unmanned experimental aircraft X-43 of complex configuration.