摘要: The growing curiosity of finding 'Earth-like' conditions in space and establishing settlements amplifies Mars exploration. Martian atmosphere comprises Carbon dioxide, Nitrogen, Argon, and Oxygen, with the Carbon dioxide content d... 展开 The growing curiosity of finding 'Earth-like' conditions in space and establishing settlements amplifies Mars exploration. Martian atmosphere comprises Carbon dioxide, Nitrogen, Argon, and Oxygen, with the Carbon dioxide content dominating. Hence, the space vehicles entering the Martian atmosphere will encounter a different environment than Earth's. Previous studies have reported that these vehicles must have blunt fore-body to encounter significant aerodynamic drag for self-assisted landing. The thermal protection system protects the vehicle's body from aerodynamic heating due to the high drag during descent. Hence, it is essential to obtain insight into the surface heating of these vehicles for designing and developing a compatible thermal protection system. The present study involves the numerical investigation of convective heating flux in a blunt cone subjected to a flow of Mach 5.8 at 0~0 angles of attack. Effects of stagnation enthalpy and medium on surface heating are observed. These flows have considerably high kinetic energy dissipation, leading to a very high temperature in the shock and boundary layers. The temperature can be high enough to cause the dissociation of the gas molecules. Hence, we are utilizing an in-house developed code to analyze the effect of the dissociation of carbon dioxide at high enthalpies. 收起