Abstract
A numerical study of damping effects on aircraft wings caused by liquid sloshing inside the fuel tanks has been performed. To model this phenomenon, a tank-fluid system is vertically excited with a periodic law of motion. The work has two parts. In the present Part I, a mathematical formalism of the global energy balance in different frames of reference is provided. Then, an enhanced Smoothed Particle Hydrodynamics model, (delta-LES-SPH), has been applied for the simulation of this violent flow. Multiple energy dissipation mechanisms such as liquid impacts and turbulence are discussed. Comparison with experimental results and the fluid-structure interaction case is carried out in Part II.
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