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Results of an icing analysis of the NASA S3 Icing Research Aircraft will be presented along with the latest improvements to the LEWICE3D ice accretion program. The icing results include collection efficiency and ice shape calculations for the S3. Recent improvements to the roughness and ice density models, performance and accuracy of the overall collection efficiency algorithm, and to the user interface for the LEWICE3D program will be discussed.

Three-dimensional simulations of the Honeywell ALF502 low pressure compressor (sometimes called a booster) using the NASA Glenn code GlennHT have been carried out. A total of eight operating points were investigated. These operating points are at, or near, points where engine icing has been determined to be likely. The results of this study were used, in a companion paper, for further analysis such as predicting collection efficiency of ice particles and ice growth rates at various locations in the compressor. In an effort to minimize computational effort, inviscid solutions with slip walls are produced. A mixing plane boundary condition is used between each blade row, resulting in convergence to steady state within each blade row. Comparisons of the results are made to other simplified analysis. An additional modification to the simulation process is also presented.