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CFD icing analysis steps on a three dimensional, swept, tapered and twisted wing.

Windt, Lennart van der (2017) CFD icing analysis steps on a three dimensional, swept, tapered and twisted wing.

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Abstract:In this work, the use of OpenFOAM is investigated as a tool for icing analyses on aircraft parts. In this work, a three dimensional, tapered, swept and twisted wing is modelled. The open source CFD package OpenFOAM is used to test several steps in an icing analysis: meshing, aerodynamics and impingement. Actual icing was not investigated due to time restrictions. It was found that OpenFOAM’s built-in mesher snappyHexMesh is very sensitive to imperfections in the used geometry file. Small anomalies on the surface resulted in bad meshing behaviour near the surface. Layers added to resolve the boundary layer better became distorted or were not added at all by the mesher. As such, the resulting mesh was of questionable quality. An aerodynamic solution could be computed very fast, using a steady state solver (simpleFoam) to generate a first approximate solution, after which a transient solver (rhoPimpleFoam) was used to compute a final aerodynamic solution. Impingement was calculated using uncoupledKinematicParcelFoam, which is a Lagrangian multiphase solver. It was found that this solver produced some unexpected results, of which no root cause was found. It is recommended to investigate the meshing problems and the impingement results further. Also, the performance of the actual icing solver in OpenFOAM needs yet to be tested for performance.
Item Type:Internship Report (Master)
Faculty:ET: Engineering Technology
Subject:52 mechanical engineering
Programme:Mechanical Engineering MSc (60439)
Keywords:in-flight icing, CFD, OpenFOAM
Link to this item:http://purl.utwente.nl/essays/74238
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