Submit Manuscript | http://medcraveonline.com Abbreviations: RANS, reynolds average navier-stokes; TE, trailing edge; CFD, computational fuid dynamics; LE, leading edge; AIS, anti-icing system; WLE, wing leading edge; IRT, icing research tunnel Introduction When an aircraft fies through clouds under icy environments, supercooled droplets of water at temperatures below the freezing point can affect its surfaces and cause ice accretion. A mixture of freezing circumstances and moisture content in the atmosphere causes icing on aircraft. Protection of an aircraft from the adverse effect of ice accretion on wing surface is a signifcant design problem for fight. Ice formation is a very dangerous condition, as it affects the aerodynamic wing design and this state is important to prevent. 1 In recent years, the practical concept of icing and anti-icing, such as the impingement of supercooled large droplets (SLD), the fow and heat transfer of runback water in glazing or mixing icing, and the effect of roughness on ice accretion have all been gradually developed to enhance icing detection or anti-icing system design. 2 If moisture affects an aircraft’s forward facing surfaces and these surfaces are at or below 0°C, an ice build-up may seriously change the aerodynamic characteristics. This refers in particular to tiny objects with greater catch rate effectiveness than large ones, since tiny quantities of ice will generate relatively larger shape changes, posing a signifcant performance and safety risk. The geometry of anti-icing system Figure 1 consists of a piccolo tube with three rows of round jets inside the wing based on airfoil NACA23012 Figure 2 According to Illinois University database at Urbana-Champaign. 3 The aircraft propulsion system is penalized by the anti-icing scheme because it uses hot bleed air to prevent the ice formation on the wing. 4,5 Therefore, it is very essential to understand the demands for hot airfow by defning the processes of the heat transfer of impingement jet. Figure 1 NACA 23012 airfoil wing section. 3 Figure 2 anti-icing system. 5 The real quantity and shape of the ice build-up depend on surface temperature resulting from an energy equilibrium resulting from heat input from viscous or kinetic air heating, water droplet kinetic heating and latent fusion heat, and losses from evaporation or sublimation, convection and heating of the impinging particles. The CFD studies described here have been conducted for dry external fow conditions. In the calculations carried out using the commercial Navier-Stokes code ANSYS, a 124-mm Partial Span Model was used. Figure 3,4,5 shows the geometric specifcations for the designs. Int Rob Auto J. 2020;6(2):60‒66. 60 ©2020 Hassaani et al. This is an open access article distributed under the terms of the Creative Commons Attribution License, which permits unrestricted use, distribution, and build upon your work non-commercially. Numerical investigation of thermal anti-icing system of aircraft wing Volume 6 Issue 2 - 2020 Ahmed Hassaani, 1 Ahmed F. Elsayed, 2 Essam E. Khalil 3 1 PhD student, Department of Aeronautical Engineering, Institute of Aviation and Technology, Egypt 2 Professor of Mechanical Engineering, Zagazig University, Egypt 3 Professor of Mechanical Engineering, Cairo University, Egypt Correspondence: Ahmed Hassaani, PhD student, Department of Aeronautical Engineering, Institute of Aviation and Technology, Cairo, Egypt, Tel +201003707525, Email Received: January 08, 2020 | Published: May 05, 2020 Abstract There has always been an ongoing effort to improve aircraft anti-icing systems. Aircraft Icing poses a dangerous to the performance and safety, so it has a great concern for the airplane manufacturing and Airliners. The geometry of anti-icing system consists of a piccolo tube inside a swept wing with three rows of round jets based on NACA 23012 air foil. Commercial ANSYS CFD software is used to solve a compressible internal airfow, an external cold airfow and the thermal conduction in the solid skin. By modelling only the effects of conductive, viscous and convective heat transfer in a dry atmosphere the complexity of this procedure conjugate heat transfer is reduced. Used three dimensional Navier-Stokes computer code to simulate the jet fow impinging with circular confguration and heat transfer. The fow feld of all turbulent regions was modelled by using the two- equation k ω Shear Stress Transport (SST) turbulence model. This research work indicates a strong potential of using CFD in dynamic of partial wing segment including thermal anti-icing system model at different external fow parameters development and validation. Keywords: computational fuid dynamics, wing anti-icing, conjugate heat transfer, thermal anti-icing, bleed air International Robotics & Automation Journal Research Article Open Access