Automatic Mesh Optimization for Wing-Fuselage Juncture Flow Separation Predictions

This work applies an automated mesh optimization technique in combination with a selection of turbulence models for the simulation of the NASA Juncture Flow experiments, and assesses the ability to accurately and efficiently capture the salient flow features, with particular focus on the separated flow near the trailing edge of the wing-body junction. The mesh optimization is based on smoothing an estimated solution error and uses anisotropic mesh refinement to maximize computational efficiency. It is applied in conjunction with the general-purpose k-ω Shear Stress Transport turbulence model and two Reynolds Stress turbulence models, RSM-BSL and BSL-EARSM.