NUMERICAL SIMULATION OF SHOCK-STALL FLUTTER OF A HIGH-ASPECT-RATIO FORWARD-SWEPT WING

摘要

In order to understand the unusual flutter phenomenon observed in experimental transonic flow for a high-aspect-ratio forward-swept wing, numerical simulations have been conducted using a 3D Navier-Stokes code. The simulations have confirmed that the flutter is a single-degree-of-freedom flutter of the first bending mode in which shock-induced flow separation plays a dominant role. The simulations have also clarified the detailed effects of Mach number and dynamic pressure (particularly the mass ratio) on this type of flutter.