Experimental and Numerical Aeroelastic Analysis of Airfoil-Aileron System with Nonlinear Energy Sink
Recent studies on nonlinear passive absorbers present high control efficiency for broadband frequency range with low added mass. This work presents a configuration of an airfoil typical section where the flap is considered as a Nonlinear Energy Sink (NES), which adds zero mass and has a cubic stiffness. An aeroelastic test-bench was created and characterized for linear and nonlinear structural configurations and tested in a subsonic wind-tunnel experimental campaign. The strongly nonlinear hardening stiffness is obtained by using linear springs and geometric nonlinearities. For the nonlinear tests, several Limit Cycle Oscillation (LCO) and subcritical and supercritical Hopf bifurcations were observed. Numerical analysis was also carried out for both linear and nonlinear cases using: Unsteady Vortex Lattice Method (UVLM) and Theodorsen theory (both low fidelity), Euler (medium fidelity) and Reynolds-Averaged Navier Stokes (high fidelity) methods. The numerical methods present good agreement, within the limits of each approach, and correspond with the experimental data. Using the NES, a gain of flutter speed is reached compared to the linear flap restoring force configuration.
KeywordsAeroelasticity Unsteady aerodynamics Flutter LCO Nonlinear dynamics
The authors would like to acknowledge the Natural Sciences and Engineering Research Council of Canada and ISAE-Supaero for the funding. The work benefited from the advices of Simon Bourgault-Côté and Matthieu Parenteau regarding the software NSCODE and UVLM, respectively.
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