Design of the nose cone of a transonic sounding rocket

This thesis aims to enclose my work carried out at the Technical University of Munich, within the WARR - Rocketry group, during the Erasmus exchange. The main objective is to design the nose cone of a liquid-propelled sounding rocket which, due to further constraints, finds itself flying in the transonic regime. For this reason, the parameter to be optimised is the aerodynamic resistance, but the final decision will have to take into account a variety of considerations. The methods used in this thesis are an initial research in the literature, in order to identify the most performing geometries in the transonic regime, and subsequently a computational fluid dynamics analysis, first two-dimensional and then three-dimensional, to refine the design.