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 airflow, an external cold airflow 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 flow impinging with circular configuration and heat transfer. The flow field 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 flow parameters development and validation.

Keywords

computational fluid dynamics, wing anti-icing, conjugate heat transfer, thermal anti-icing, bleed air, temperature, freezing point, aircraft, glazing, mixing, icing, evaporation, sublimation, particles, energy