A Study on Steady-State Flow Simulation of Aircraft Wake Using Anisotropic Mesh Adaptation

Accurate prediction of aircraft wake is crucial for the aerodynamic design and performance evaluation of aircraft. This is especially essential for innovative configurations where the wake interacts with aft-mounted propulsors. This study investigates the capability of steady turbulent flow simulation to predict wing and aircraft wake using anisotropic mesh adaptation. Anisotropic solution-adapted meshes are generated around two-dimensional (flat plate and airfoil) and three-dimensional (wing and aircraft) geometries. Two-dimensional simulation results agree well with both reference fixed mesh results and the theoretical profile. The total pressure distribution in the wake is also accurately predicted. Three-dimensional simulation results also exhibit a less diffused total pressure distribution and a clearly resolved wing-tip vortex. More accurate prediction of the boundary layer flow is expected to enhance overall flow‑field and drag prediction.