In hypersonic aerothermodynamics, accurately predicting radiative heat transfer at the stagnation point of re-entry vehicles is paramount for the design of effective thermal protection systems. This thesis presents the development of a one-dimensional numerical code, implemented in MATLAB, aimed at simulating the radiative heat flux along the stagnation line of a spherically shaped re-entry capsule. Approximate methods are utilized to model the complex interactions between the high-temperature gas and the vehicle surface, facilitating rapid yet reliable predictions of radiative heat loads. This work has been carried out in collaboration with Thales Alenia Space Italia, where simulations were performed using Metacomp’s ICFD++ to compare results and validate the developed numerical model.