Abstract
One of the key concerns in aircraft flight is the accumulation of ice on the wing leading edge and nacelle lip-skin. It is well known that ice accretion may dangerous to the aircraft since it severely degrades the aerodynamic performance of aircraft. As a consequence, the piccolo tube anti-icing system is installed by the aircraft manufacturer inside wing leading edge and nacelle lip-skin in order to prevent ice accumulation. However, the hotspots from piccolo tube anti-icing system potentially defect or destroy material of nacelle lip-skin. Therefore, in present work, the numerical investigation with one-way fluid-structure interaction (FSI) has been carried out to study the effect of Reynolds number based on effective-impingement-surface of piccolo tube anti-icing system on the maximum thermal stress and strain of nacelle lip-skin for several aluminum series. The simulation results reveal that the maximum strain increases with the Reynolds number. For the stress analysis, the maximum stress increases to the peak value, then it gradually decreases with Reynolds number. Among the materials have been studied, aluminium 7 series shows the highest maximum stress and maximum strain for all Reynolds number and hotspot temperature, however, aluminium 1 series produces the lowest maximum stress and maximum strain.
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