Continuum Aeroelastic Model for a Folding-Wing Configuration

Abstract

An aeroelastic model and analytical solution methodology are developed to find the flutter solutions for the continuous representation of a two-segment uniform folding wing. The model is developed such that different parameters can be easily modified to examine changes in the flutter solutions. Of these parameters, the fold angle between the inboard and outboard wing segments is of particular interest for understanding the fundamental aeroelastic behavior of folding wings. The results are presented as the evolution of the aeroelastic frequencies and damping with respect to the freestream velocity. This enables the determination of flutter speeds and modes. Three aerodynamic models of increasing sophistication are considered, which underscore the sensitivity of the flutter solution to unsteady effects. The capabilities of the aeroelastic analysis are demonstrated for a test case in which the flutter speed is plotted versus fold angle for three aerodynamic models.