Unsteady computational fluid dynamics calculations are presented of the abrupt wing stall phenomenon on the preproduction F/A-18E using detached-eddy simulation. Detached-eddy simulation combines the efficiency of a Reynolds-averaged turbulence model near the wall with the fidelity of large-eddy simulation in separated regions. Because it uses large-eddy simulation in the separated regions, it is capable of predicting the unsteady motions associated with separated flows. Detached-Eddy Simulation has been applied to predict the unsteady shock motion present on the F/A-18E at transonic speeds over several angles of attack. Solution-based grid adaption is used on unstructured grids to improve the resolution in the separated region. Mean flow results are compared to leading Reynolds-averaged models showing improved predictive capability. Unsteady surface pressures are shown to be in good agreement with experimental measurements. The presence of low-frequency pressure oscillations due to shock motion in the current simulations and the experiments motivated a full aircraft calculation, which showed low-frequency high-magnitude rolling moments that could be a significant contributor to the abrupt wing stall phenomenon.

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