Flow field prediction of an orbiter entering the Mars atmosphere

Based on the hypersonic entry in the Entry-Descending-Landing procedure, the three-dimensional Navier-Stokes equations are solved by a parallel code to analyze the flow field structures, aerodynamic characteristics and their variation patterns of the Mars Science Laboratory entering the Martian atmosphere with and without the chemical reaction models. The analysis shows that parameters of the thermal dynamics and the transportation have an effect on the position and intensity of the shock wave. As a result of the chemical non-equilibrium effect, the shock layer is strongly compressed, the stagnation pressure decreases and the maximum temperature behind the shock is highly reduced where large number of CO₂ is dissociated. Results of the streamlines on symmetric plane and in space reflect the complicated three-dimensional separation flows in the wake.