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In the framework of the SUNSET2 program, ice accretion numerical tools were assessed against experimental data. The database of ice shapes was generated on CRM-like swept-wings in NASA’s IRT wind tunnel. This paper discusses calculations of ice accretion on some cases of this database with the ONERA’s 3D ice accretion suite, called IGLOO3D. This tool is described in the first part of the paper. It is designed to couple three codes which solve the air flow (Navier-Stokes solver), the trajectories of water droplets (Eulerian or Lagrangian solver) and the ice accretion (Messinger approach), respectively. The coupling is made in a one-way manner by exchanging CGNS files. IGLOO3D is modular and makes it possible to couple any code as long as it reads and produces CGNS files. The ice thickness predicted by IGLOO3D is compared against the experimental ice shapes and the LEWICE3D results.

Numerical simulation of ice accretion on aircraft surfaces necessitates a good prediction of wall friction coefficient and wall heat transfer coefficient. After the icing process begins, surface roughness induces a high increase of friction and heat transfer, but simple Reynolds analogy is no longer valid. An experimental campaign is conducted to provide a database for numerical model development in the simple configuration of a heated flat plate under turbulent cold airflow conditions. The flat plate model is placed in the centre of the test section of a wind tunnel. The test model is designed according to constraints for the identification of friction and heat transfer coefficients. It includes three identical resin plates which are moulded to obtain a specified roughness on the upper surface exposed to the flow. Only the 3rd resin plate is heated on its lower face by an electrical heater connected to a temperature regulator.