Aerothermal Analysis of a Space Rocket Nose Cone during Hypersonic Ascent Phase

In this paper an aerothermal analysis is conducted to estimate the maximum stagnation point heat flux at the nose cone tip of a space-faring rocket vehicle under development by a student team and expected to travel at hypersonic speed during its ascent phase. A one degree of freedom trajectory analysis is conducted from rocket preliminary configuration to ascertain the maximum-heating ascent trajectory. Engineering stagnation point heat transfer models and CFD simulations are then used in a two-pronged approach to evaluate the heat flux at the instant of maximum aerodynamic heating. From here, preliminary analysis and recommendations are made for the Thermal Protection System that may be used for the nose cone tip.