SPH simulation of vertical high-speed jet flow from a circular nozzle with stagnation pressures prediction

The wings of large civil passenger aircrafts, whichare designed to withstand the loads occurring from atmosphericgusts and turbulence to landing impacts, still demand furtherresearch. This goal will be achieved through investigating thedamping effect of sloshing on the dynamics of flexible wing-likestructures carrying liquid via the development of experimentalset-ups complemented by numerical models. The aim of this workis to analyze the effect of sloshing in reducing the design loadson aircraft structures using SPH as the main numerical tool.The first step of this research was performed inside the AirbusProtospace Lab in Filton (UK), where a scaled model of theproblem was tested. The wing is represented by a cantilever witha liquid tank attached at its tip. The behaviour of the system oncedeformed and released and the accelerations at the free end ofthe beam were registered for different configurations.In this work, a numerical model of a fully coupled fluid-structure interaction problem is developed. In order to un-derstand and analyse the damping mechanisms, the structureis modelled through beam theory and solved by two differentmethods: a mass-spring-damper system and modal analysis.For the fluid, the ?-LES-SPH model is used, which has beenimplemented for the boundary integrals methodology in orderto simulate complex geometries.A set of cases are simulated in order to reproduce trendsnoticed in the experiments, including different inner tank con-figurations, for the two beam models tested. SPH as numericaltool demonstrates that the presence of liquid in tanks attachedto flexible structures introduces a damping effect.