Icing calculations on a typical commercial jet engine inlet nacelle

A procedure is presented to analyze a commercial jet engine inlet during icing. The essential steps in the numerical simulation are discussed: flowfield calculations, determination of droplet trajectories hitting the surface, and computation of the heat transfer phenomena. A three-dimensional flowfield solver utilizing the panel method was found to be adequate for modeling noncomplicated engine inlet nacelles at subsonic speeds. Droplet trajectories were produced using a three-dimensional grid-based code. Predicted collection efficiencies were in good agreement with experimental results. Heat transfer calculations are performed with the NASA Lewis ANTICE code. Two example cases are presented.