As missions to Mars become more complex, new technology is needed to meet the required objectives. Aeroshell shape optimization has the potential to improve current technology so that these new objectives can be met. This work outlines an optimization methodology using gradient-based optimization strategies and CFD to determine optimal aeroshell shapes in hypersonic entry conditions. Pareto fronts are generated in a laminar perfect gas flow, a turbulent perfect gas flow, and a turbulent Mars 9-species atmosphere. The optimal capsules generated using the Mars atmospheric model show a significant reduction in heating from the MSL capsule. These optimal shapes are spherical Apollo-like capsules which reduce the maximum heating to the forebody of the capsule by over 80 W=cm2 while still maintaining similar aerodynamic characteristics. This significant reduction in heating can allow for thinner and potentially lighter TPS materials. The reduction in TPS mass allows for an increase in payload mass while still maintaining a constant ballistic coeffcient.