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Performance simulation method of wing anti-icing system for civil aircraft was introduced. The typical method of model simplification and simulation condition parameter calculation was included to carry out the temperature distribution and water film thickness distribution of wing anti-icing cavity skin surface for different calculation condition cases. The result shows the skin temperature of wing anti-icing area for a certain civil aircraft is greater than the freezing point and dry evaporation on the upper surface of skin, with wet evaporation on lower surface, satisfying the anti-icing performance. The performance simulation method of wing anti-icing system provides reference for engineering research of wing anti-icing system development for civil aircraft.
Inspec keywords: evaporation; heat transfer; freezing; aircraft; temperature distribution; aerospace components; water; ice
Subjects: Heat and thermodynamic processes (mechanical engineering); Solid-liquid transitions; Thermodynamics; Industrial processes; Products and commodities; Convection and heat transfer; Fluid mechanics and aerodynamics (mechanical engineering); Aerospace industry; Mechanical components; Applied fluid mechanics