Experimental and Theoretical Study on Aeroelastic Response of High-Aspect-Ratio Wings

TLDR

The study combines an experimental high‑aspect‑ratio wing model tested in a wind tunnel with a theoretical framework that couples nonlinear beam equations to the ONERA stall model, using dynamic perturbation analysis and time‑domain simulation to predict flutter boundaries and limit‑cycle oscillations. Experimental and theoretical results agree well for static aeroelastic deformation, flutter onset, and the amplitude and frequency of limit‑cycle oscillations.

Abstract

An experimental high-aspect-ratio wing aeroelastic model with a slender body at the tip has been constructed, and the response due to flutter and limit-cycle oscillations (LCO) has been measured in a wind-tunnel test. A theoretical model has been developed and calculations made to correlate with the experimental data. Structural equations of motion based on nonlinear beam theory are combined with the ONERA aerodynamic stall model to study the effects of geometric structural nonlinearity and steady angle of attack on flutter and LCO of high-aspect-ratio wings. Static deformations in the vertical and torsional directions caused by a steady angle of attack and gravity are measured, and results from theory and experiment are compared. A dynamic perturbation analysis about a nonlinear static equilibrium is used to determine the small perturbation flutter boundary, which is compared to the experimentally determined flutter velocity and oscillation frequency. Time simulation is used to compute the LCO response. The results between the theory and experiment are in good agreement for static aeroelastic response, the onset of flutter, and dynamic LCO amplitude and frequency.