Abstract
In order to understand the unusual flutter phenomenon observed in experimental transonic flow for a high-aspect-ratio forward-swept wing, numerical simulations are conducted using a 3D Navier-Stokes code. The simulations confirm 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 also clarify the detailed effects of Mach number and dynamic pressure (particularly the mass ratio) on this type of flutter.
