INITIAL EXPERIMENTAL ANALYSIS OF DAMPING DUE TO LIQUID SLOSHING IN A SCALED AIRCRAFT WING MODEL Article Swipe
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· 2022
· Open Access
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· DOI: https://doi.org/10.5281/zenodo.7198068
· OA: W4306195268
Fuel sloshing inside aircraft wings can potentially increase the net damping of the wing structure. Building upon previous work on simpler sloshing systems, we present a scaled research wing prototype equipped with a fuel tank that allows the observation of liquid sloshing and quantification of induced dynamic effects. Experiments were conducted at 50% filling level and the equivalent dry case with frozen mass. We demonstrate substantial additional damping effects in multiple frequency components when liquid is added inside the tank. The dissipative effect is most noticeable in the first frequency component with deformations typical of the first bending mode of the structure, as the damping ratio was found to be substantially increased in the sloshing case regardless of the amplitude of motion.
