Session: 7.1 - Heat and Mass Transfer in multiphase flows

Paper Number: 158739

158739 - Ice Accretion Analysis on NACA0012 Airfoil With Conjugate Heat Transfer 

Abstract: 

Ice accretion on aircraft surfaces poses significant threats to aerodynamic efficiency and flight safety. This occurs when supercooled droplets impact the aircraft, forming mainly two distinct types of ice: rime ice, which forms at very low temperatures (below -10°C), creating a rough, porous, and brittle layer; and glaze ice, which forms between -3°C and -10°C, producing dense, smooth, and irregular structures that significantly disrupt airflow and increase risks. This study numerically investigates ice formation on aerospace-grade aluminum alloys using computational simulations to model airflow, droplet trajectories, and phase change processes. Key factors, such as surface roughness, liquid water content (LWC), mean volume diameter (MVD) of droplets, and air temperature, are analyzed to predict the type, geometry, and weight of ice on NACA0012 airfoil wings. Aerodynamic penalties from ice accretion—such as increased drag, reduced lift, and potential stall conditions—are quantified through simulations. In addition to enhance the accuracy of these simulations, the Conjugate Heat Transfer (CHT) method is utilized, coupling thermal interactions between solid surfaces and surrounding fluid domains (e.g., airflow). Finally, power requirements for Ice Protection Systems (IPS) are evaluated to optimize de-icing efficiency while ensuring flight safety.  This integrated approach provides valuable insights into the behavior of ice accretion on aluminum alloys and supports the development of energy-efficient de-icing strategies, contributing to improved flight safety and aircraft performance.

Presenting Author: Moussa Tembely Concordia University

Presenting Author Biography: