Aeroelastic flutter analysis in viscous flow: continuum models

Abstract

A continuum model of wing structure aeroelastic response in viscous air flow with nonzero flow on the wing show, including energy conservation law, showing that there is no lift generated in contrast to the inviscid case. This would appear to be consistent with the Prandtl Boundary Layer theory where the pressure gradient normal to the wing is set to be zero but of course also the speed on the wing.