Abstract
Icing simulations involving super-cooled large droplets (SLDs) on a NACA0012 airfoil and a commercial axial fan were performed considering the characteristic behavior of SLD icing (i.e., splash-bounce, deformation, and breakup). The simulations were performed considering weak coupling between flow field and droplet motion. The flow field was computed using the Eulerian method, wherein the droplet motion was simulated via the Lagrangian method. To represent the ice shape, an extended Messinger model was used for thermodynamic computation. The ice shape and collection efficiency of the NACA0012 airfoil derived using the icing simulation exhibited a reasonable agreement with the existing experimental data. The icing simulation results for the axial fan, in terms of distribution of ice on the blade and its influence on the flow field, indicated that flow separation occurred, and the mass flow rate of the flow passage decreased. Moreover, the splash and bounce phenomena considerably influenced the icing process; however, the effect of the deformation and breakup phenomena was negligibly small. In terms of the effect of the SLDs on the icing phenomena, it was noted that, with the decrease in the SLD temperature (from −5 °C to −15 °C), the number of adhering SLDs increased, whereas the number of splashing and bouncing SLDs decreased.
Highlights
The icing phenomenon, which commonly occurs in aircraft and involves super-cooled droplets impinging and accreting on a solid surface, has been recognized as a critical safety problem.In particular, icing induced in pitot tubes may lead to an incorrect indication
Icing simulations were performed considering the specific phenomena of super-cooled large droplets (SLDs) i.e., splash, bounce, deformation, and breakup
The results of the SLD simulation for NACA0012 were in reasonable agreement with the experimental data in terms of the ice shape
Summary
The icing phenomenon, which commonly occurs in aircraft and involves super-cooled droplets impinging and accreting on a solid surface, has been recognized as a critical safety problem. Zhang and Liu [11] experimentally investigated the effect of the droplet size on the thermodynamics pertaining to the SLD impingement and reported that the droplet size considerably influences the heat transfer between the film–substrate interfaces; this aspect was verified by a theoretical analysis. They developed an impinging heating model and applied it to the SLD icing simulation. Wang et al [12] developed a splashing model for the SLD impingement and performed icing simulations for clean and iced NACA23012 airfoils, based on the Lagrangian approach. In the icing simulation for the fan blade, the variation in the flow field and mass flow rate owing to the icing and the influence of the SLD events and SLD temperature on the ice shape were investigated
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
