ICING CALCULATIONS ON A TYPICAL COMMERCIAL JET ENGINE INLET NACELLE

A procedure is presented to analyze a commercial jet engine inlet duri ng icing. The essential steps in the numerical simulation are discusse d: flowfield calculations, determination of droplet trajectories hitti ng the surface, and computation of the heat transfer phenomena. A thre e-dimensional flowfield solver utilizing the panel method was found to be adequate for modeling noncomplicated engine inlet nacelles at subs onic speeds. Droplet trajectories were produced using a three-dimensio nal grid-based code. Predicted collection efficiencies were in good ag reement with experimental results. Heat transfer calculations are perf ormed with the NASA Lewis ANTICE code. Two example cases are presented .