Abstract
A series of calculations are carried out for a Mars Science Laboratory entry vehicle heat shield and compared with tests carried out in the Arnold Engineering Development Center for Mach 8 and 10 and a range of Reynolds numbers. Three turbulence models are employed that are implemented in the LAURA code: the Cebeci-Smith algebraic model, the 98 Wilcox k − ω model, and the k − ζ model. In general, good agreement is indicated with turbulent predictions. Because the flow is attached, the algebraic model performs as well as other models.
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