This paper deals with the aerodynamic and aerothermodynamic analysis of two manned braking systems entering the Mars atmosphere, aiming to support design studies of planetary entry systems. Two vehicle configurations have been analyzed: a capsule type configuration and a lifting body with rounded edge delta-like cross section. Several fully three-dimensional computational fluid dynamics analyses, both for perfect gas model and for non-equilibrium reacting gas mixture model, have been performed to assess the flowfield environment around the vehicle in the framework of a Mars entry scenario. A wide range of flow conditions, including different angles of attack, various Mach numbers and Reynolds numbers, have been investigated and compared. The effects of finite-rate chemistry and wall heterogeneous reactions on vehicle aerothermodynamics and aerodynamics are highlighted. The results show a clear influence of real-gas effects on the aerodynamic drag and on the pitching moment, whereas the lift is only slightly affected. Moreover, the comparison between the results of computations with non-catalytic wall and for fully catalytic wall highlights that chemical reactions at vehicle surface play a significant role for the determination of the vehicle thermal load.
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