Simulation of the Transonic Truss-Braced Wing for High-Lift configuration at Mach 0.2 using USM3D-Mixed Element Solver

Numerical simulations for the high-lift configuration of the Transonic Truss-Braced Wing are carried out using USM3D-ME using Unsteady Reynolds Averaged Navier-Stokes turbulence models at Mach Number of 0.2 and a Reynolds Number of 0.98x106. Results from numerical simulations are compared against experimental studies carried out in the NASA 14x22 Wind Tunnel at Langley Research Center. The simulations are in close agreement with experiments for low angles of attack. Major discrepancies are observed for the stall region. The largest deviation from experiments occurs outboard of the strut-wing intersection which suggests incorrect momentum transfer in the spanwise direction. It is concluded that although industry-standard RANS models are able to predict flow features associated with a high-lift configuration with some accuracy, improved turbulence models with scale resolving capabilities should be considered especially in the stall and post-stall region for accurate prediction of flow physics.