During atmospheric re-entry, a space vehicle must withstand an extreme aerodynamic heating environment, which may lead to surface temperatures above 3000K. Thermal Protection Systems (TPS) were designed to protect the underlying metallic structure. To investigate ablation of the TPS, groundbased experiments in impulse duration facilities can be conducted to understand the aerothermodynamic surface ablation. Impulse duration facilities can reproduce a realistic re-entry flow but representative surface temperatures were only possible by pre-heating the test model (D'Souza, 2010). In previous implementations, prototypes with rectangular cross sections were successfully pre-heated to above 3000K using electrical heating (Zander, 2013). However, this does not match the geometry of real re-entry vehicles (e.g. Apollo, Stardust) which were generally blunt bodies with hemispherical nose segments. This discrepancy was addressed by this thesis which aims to design a hemispherical model which can be electrically preheated to realistic surface temperatures of approximately 3000K. The heated model was to be fabricated from graphite, as this was representative of the char layer which formed on the TPS surface after the original material undergoes pyrolysis. This thesis provided an overview on typical past methods for studying ablation in ground-testing facilities, including both longduration facilities such as arc jets and impulse facilities such as expansion tubes. The potential ablation mechanisms for carbon include oxidation, nitridation, sublimation, and mechanical spallation. Further measurements and characterisation of these processes were required to reduce TPS design uncertainties.Past re-entry spacecraft designs and studies typically used a blunt body design concept (Walter G. Vincenti, 2007), and the role of the blunted nose was discussed. In the terms of geometry design, for this work the electrical preheating calculations were validated against past experiments with rectangular cross sections. Secondly, the electrical heating and radiative cooling of hemispherical geometries were theoretically investigated to determine a cross-sectional profile which provides a uniform temperature distribution, for various grades of graphite. These predictions were then validated using the finite element method, allowing the most suitable material to be selected. Eventually, a hemispherical geometry was designed and simulated which able to preheat evenly on its out most surface.