Numerical solutions for hypersonic aerothermodynamics of Mar's Pathfinder at Mach number 10 have been computed using the one-equation Spalart-Allmaras turbulence model and the second order MUSCL upwind scheme, AUSM+ scheme combined with LU-SGS implicit iteration has been used here. The numerical results derived from calorically and thermally perfect gas models have been compared with experimental data. Computed heating rates distributions with thermally perfect model are in good agreement with the experiment, however, those in separated zones are poorly predicted. It is seen that thermodynamic properties of hypersonic flows except the separated zones can be correctly simulated with this method if the mesh is appropriately designed, in particular, when the grid resolution near wall is sufficient.