Computational-fluid-dynamics-based axisymmetric aeroshell shape optimization in hypersonic entry conditions

An optimization routine using computational fluid dynamics is outlined and applied to axisymmetric aeroshells in hypersonic entry conditions. Two objectives are considered in the optimization: minimizing the peak heat flux at the wall and maximizing the drag coefficient. These objectives are scaled and combined intoa single scalar quantity called the objective function. A weight is applied to each objective to study the tradeoff effect that the objectives have on the shape. A Pareto frontis produced by varying the weight between 0 and 1 and plotting theoptimal shapes. Pareto fronts are generated in three environments: laminar perfect gas air, turbulent perfect gas air, and a nine-species Mars environment. The optimal aeroshells are compared with the Mars Science Laboratory aeroshell. The optimal aeroshells generated in the two perfect gas air environments compare similarly with the Mars Science Laboratory aeroshell. The optimal aeroshells generated in the Mars atmosphere show significant deviations from the Mars Science Laboratory aeroshell. Significant reductions in heat flux and small increases in drag coefficient are seen from the optimal aeroshells. These optimal aeroshells are spherical Apollo-like aeroshells.