الفهرس 
Title: Numerical Study of Aircraft Wing Anti-Icing System Using Bleed Air from Turbo-Fan Engine
ContentsOnly 14 pages are availabe for public view
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Abstract
A generally utilized technique in aeronautical industry to overcome icing accretion phenomena is to utilize a bleed hot air for anti-icing system in view of its efficiency and simplicity. In the current work, an anti-icing structure for a usual aircraft wing of NACA 23014 airfoil profile. 3D simulations were done to get the temperature and heat flux distribution on wing outer surface for a constant airplane speed of 0.85 Mach, [2% to 6%] bleed air with high pressure and temperature, [15 to 60 degree] jet impingement angle and [4.5 to 9.01mm] distance between piccolo tube and wing inner surface in order to investigate suitable geometry and mass flow rate for avoiding icing accretion, a performance studding were done on turbofan engine to study effect of bleed air on engine performance parameters. In this research was shown that heated surface on leading edge was increased with jet impingement angle and approaching of piccolo tube to leading edge, by comparing 60-degree jet impingement angle with 15, 30 and 45-degree jet impingement angles, it has been found that heated areas on upper surface increased by 37.7%, 26% and 13% respectively, heated areas on lower surface increased by 36.24%, 25% and 6.2 % respectively