Stall Flutter of the Benchmark Supercritical Wing at High Angles of Attack

Abstract

The Benchmark Supercritical Wing (BSCW) is the current testbed for the third Aeroelastic Prediction Workshop (AePW-3). The focus of the AePW-3 was set on evaluating the flutter-onset boundary at a transonic Mach number of 0.8 and high angles of attack. The goal of the current study is to investigate the physical properties of the two flutter mechanisms that the BSCW experiences: 1) conventional heave-pitch coalescence flutter at low angles of attack and 2) stall flutter at high angles of attack. These two conditions are studied by coupled Unsteady Reynolds-Averaged Navier-Stokes aeroelastic simulations. Simulations are presented and analyzed at a single Mach number and two angles of attack to further illustrate the distinction between the two flutter mechanisms encountered by the BSCW. The flow field at stall flutter conditions is investigated to further shed light on the fluid-structure interaction that alters the flutter mechanism.