Unsteady aeroelastic characterization and scaling relations of flexible membrane wings

TL;DR

This study uses numerical simulations to analyze the nonlinear unsteady aeroelastic behavior of flexible membrane wings at high angles of attack, establishing scaling relations and providing insights for improved MAV design.

Contribution

It introduces a new scaling relation for flexible wings based on dynamic equilibrium and systematically explores the effects of key parameters on aeroelastic behavior.

Findings

Time-averaged membrane deformation correlates with Weber number.

Unsteady aerodynamic forces can be controlled via membrane vibration and other parameters.

Phase diagrams reveal optimal performance envelopes and transition lines.

Abstract

We present a numerical study to characterize nonlinear unsteady aeroelastic interactions of two-dimensional flexible wings at high angles of attack. The coupled fluid-flexible wing system is solved by a body-fitted variational aeroelastic solver based on the fully-coupled Navier-Stokes and nonlinear structural equations. Using the coupled fluid-structure analysis, this study is aimed to provide physical insight and correlations for the aeroelastic behavior of flexible wings in the parameter space of the angle of attack and the aeroelastic number. The phase diagrams of the aerodynamic performance are established to obtain the envelope curves of the optimal performance and determine the transition line of the drag variation. The effects of the angle of attack and the aeroelastic number on the aeroelastic behaviors are systematically examined. The time-averaged membrane deformation is positively correlated with a non-dimensional number, the so-called Weber number. A new scaling relation is proposed based on the dynamic equilibrium between the aerodynamic force fluctuation and the combined inertia-elastic fluctuation. The unsteady aerodynamic force can be adjusted by manipulating the membrane vibration, the mass ratio, the Strouhal number and the aeroelastic number. The numerical investigations provide design guidelines and have the potential to enhance the maneuverability and flight agility of micro air vehicles with flexible wing structures.