Computational Study of Stall Flutter of the Benchmark Supercritical Wing

The paper presents an investigation of the stall flutter mechanism of the Benchmark Supercritical Wing (BSCW), performed as part of the 3rd Aeroelastic Prediction Workshop (AePW-3), high angles of attack working group. The characteristics and onset conditions of the BSCW’s stall flutter, at the examined flow conditions of Mach number of 0.8 and high angles-of-attack, are highly dependent on the numerical parameters used for the flow simulation, and specifically on the choice of turbulence model. This is because, as presented in the study, stall flutter results from flow separation and aerodynamic damping, which are highly sensitive to turbulence modeling. The goals of the current study are two-fold: 1) Investigate the effect of turbulence modeling on the stall flutter boundary prediction, and 2) Investigate the stall flutter mechanism, physical characteristics, and how they are affected by flow separation prediction in coupled Unsteady Reynolds-Averaged Navier-Stokes aeroelastic simulations. Analyzing the aeroelastic responses, aeroelastic forces, and the flow field itself for different dynamic pressures and turbulence models, we suggest the connection between the fundamental flow development and the resulting aeroelastic response at these conditions.