Aircraft De-icing Performance Analysis by an Adapted Temperature Field Analyser Program

An evaluation of a special thermal mathematical model for anti- or de-icing purposes on airfoils and air inlets of air-crafts is described. The model using finite elements includes heat transfer by conduction, high speed convection for laminar or turbulent air flow, evaporation and mass transport.

The thermal mathematical model enables us to vary flight weather conditions, contour geometries, de-icing system details and the flight design cases with the combined turbine engine performance datas. The new mathematical model delivers a detailed matrix of surface temperatures and the running wet back water. The model flexibility will be demonstrated.