CFD Investigation on Tailplane Ice Protection System

Abstract

​​In this study, the effectiveness of engine exhaust in shielding aircraft tailplanes from ice accretion a known aviation safety hazard is examined. Three sample aircraft which are Gulfstream G280, Airbus A320 and Airbus A380 were used to run Computational Fluid Dynamics (CFD) simulations, considering important parameters such exhaust temperature, plume dispersion, and flying phase. The A320 was evaluated in four operational conditions: take-off, cruise, runway roll, and taxiing. EASA Type Certificate Data Sheets were used to collect engine exhaust data in order to guarantee realistic boundary conditions. The results clearly show the differences between aircraft types. Since the engines of the A320 and A380 are situated beneath the wings, the exhaust plumes swiftly disperse beneath the tailplane, creating hardly any heating effect. Due to the absence of a tailplane ice prevention system (IPS), these aircraft would have been subject to weight and fuel penalties. The G280, on the other hand, which has engines situated on the rear fuselage, displayed some tailplane heating and plume impingement. An IPS is still necessary since this natural impact was insufficiently powerful at altitude. The distinction reflects aircraft philosophy: business jets place a higher priority on flexibility and safety margins, whereas high-volume airline aircraft are optimized for efficiency. Overall, the study confirms that exhaust heat alone cannot provide reliable ice protection. Instead, the findings point towards hybrid approaches where limited natural heating could be combined with technologies like electrothermal or bleed-air systems as a more practical way forward for future aircraft.​