Abstract
Thermal flow in an aircraft wing leading-edge anti-icing system is a complicated physical phenomenon and remains a challenging research topic of modeling and analysis. We present a complete three-dimensional simulation of a wing segment including the piccolo-type thermal anti-icing bays inside the leading edge is presented. The Navier-Stokes analysis has been conducted for the integrated internal/external thermal flows with heat conductivity through the solid skin. The fully structured zones and boundary-layer meshing have reduced the total cell number and enhanced the near-wall impingement and the heat transfer analysis. Simulation results visually reveal the hot/cold flow interactions and heat conductivity through the fluid and solid zones. The calculated leading-edge surface temperature is compared with flight-test data of a similar configuration. The computational fluid dynamics model and its analysis under different flight conditions and configuration modifications provide a valuable assessment for wing anti-icing system research and development
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