Stall Flutter of the Benchmark Supercritical Wing Using Aeroelastic Model Reduction and Tunable Turbulence Parameters
This paper investigates the flutter mechanism of the benchmark supercritical wing at Mach 0.8 with the angle-of-attack (AOA) at 1◦, 3◦ and 5◦. Nonlinear unsteady aerodynamic reduced order models (ROMs) are used which are trained using data obtained from URANS simulations with tunable turbulence parameters. The influence of steady and unsteady shock statistics, and structural damping, on the flutter dynamic pressure are systematically studied. It is demonstrated that the performance of the nonlinear ROMs for highly nonlinear stalled flow conditions is excellent. The stall flutter mechanism at AOA = 5◦ is shown to be highly sensitive to the predicted shock/separation location, and to structural damping, while coupled mode flutter at lower AOA’s is relatively insensitive to both. It is also shown that flutter/LCO is supercritical at AOA = 1◦, and subcritical at 3◦ and 5◦. The authors are grateful for the financial support provided by the Asian Office of Aerospace Research and Development (AOARD) and Air Force Office of Scientific Research (AFOSR) for project FA2386-24-1-4044: Data-Driven Reduced Order Modelling and Preliminary Experimentation for Combined Transonic Buffet and Freeplay Induced Limit Cycle Oscillations.
