Experimental and Computer Model Results for a Carbon Nanotubes Electrothermal De-Icing System 2019-01-2005
Results from three-dimensional computer models of a Carbon Nanotubes (CNT) based de-icing system are compared to experimental data obtained at UTAS-Ohio Icing Wind Tunnel (IWT). A prototype of the CNT based de-icing system being jointly developed by UTAS and EMBRAER was installed in a section of a business jet horizontal tail and tested in the IWT for a range of conditions. The 3D numerical analysis tools used in the comparisons are AIPAC and FENSAP-ICE®. The former was derived from an anti-icing model developed at Wichita State University in 2010. AIPAC uses the finite volumes method for the solution of the icing problem on an airfoil leading edge (or other 3D surfaces) and relies on CFD solvers to obtain the external flow properties used as boundary conditions. The latter is a computer code for icing simulations currently commercialized by ANSYS®. Both tools are capable of predicting 3D multi-step ice shapes under rime, glaze and mixed regimes, and can also deal with the complex dynamics of cyclic ice accretion, melting, and shedding present in the realm of aircraft electrothermal de-icing systems. Comparisons of predicted vs. experimental leading edge temperatures along time as well as intercycle and runback ice extents, positions, and thicknesses are provided. The numerical tools used have shown good agreement with the experiments, fairly capturing the most important ice shape features for aerodynamic degradation and keeping the airfoil skin temperatures predictions close to the experimental results.
Rodrigo Domingos, Gilberto Becker
Embraer, Embraer SA
International Conference on Icing of Aircraft, Engines, and Structures