Abstract
A comprehensive experimental approach to the problem of determining static stability boundary (divergence) or dynamic stability boundary (flutter) of a given multiparameter aeroelastic system in a low speed wind tunnel is presented. The experimental setup with the corresponding measurement algorithm is based on the well-known theoretical model of an elastically supported typical wing section with two degrees of freedom. The design of the experimental system makes it possible to vary structural parameters within the determined parameter space. An automated measurement algorithm for determination of static or dynamic stability boundary by monitoring the aeroelastic system response to an initial impulse in the time domain is developed. The multiparameter experimental results of the case study using a NACA 0012 airfoil are compared to the analytical solutions of the theoretical model. The comparison shows that the experimental setup represents a reliable platform for aeroelastic wind tunnel test purposes. In addition, series of experiments were conducted to investigate the effect of airfoil thickness distribution on dynamic and static stability boundary. The results are compared to those of the NACA 0012 airfoil.
Published Version
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