With the continuation of solar system exploration, regular journeys to the moon anticipated within the next decade, and missions routinely being carried out with atmospheric flight at super orbital speeds, there is a pressing need for accurate aerodynamic data for hypervelocity re-entry capsules and other hypersonic vehicles. Designing vehicles to operate in this medium presents great engineering challenges, and the advancement in technology that has allowed this progress is mirrored by advances in testing methods. This thesis used computational fluid dynamics and theoretical methods to compare the conditions experienced by the Crew Exploration Vehicle during Earth atmospheric entry to those which could be reproduced by a scaled model within an expansion tube facility that was created through binary scaling. The two cases with a wall temperature of 10,000 K were found to be closer in agreement for both the CFD and empirical methods than the case with a wall temperature of 1,000 K. Scaled model cases 1 and 2 with 10,000K wall temperatures differed to the full size vehicle by 28.45 % and 49.42 % respectively for the CFD simulations. The empirical calculations differed by 44.14 % and 71.47 % respectively. Case 2 with a 1000 K wall temperature differed by 98.94 % and 98.49 %. These results showed that increasing the wall temperature the same factor as the increase in flow temperature from the full size to scaled models did in fact improve the results. This also showed again how heavily the assumed wall temperature can influence the heat transfer results. Given all the assumptions that have gone into the simulations and calculations, the results were reasonably close in agreement and showed just how powerful the ñL scaling parameter is for simulating such harsh environments without having to conduct testing on real flight vehicles. The results also showed that the parameters calculated by the 0D analysis are an extremely effective starting point in determining the required expansion tube set up to achieve the desired testing conditions.