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Parallel solution of lifting rotors in hover and forward flight
Author(s) -
Allen C. B.
Publication year - 2006
Publication title -
international journal for numerical methods in fluids
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.938
H-Index - 112
eISSN - 1097-0363
pISSN - 0271-2091
DOI - 10.1002/fld.1277
Subject(s) - wake , polygon mesh , solver , multigrid method , grid , computer science , mesh generation , computational fluid dynamics , code (set theory) , vortex , representation (politics) , flow (mathematics) , computational science , aerospace engineering , mechanics , simulation , physics , mathematics , engineering , geometry , mathematical analysis , structural engineering , computer graphics (images) , partial differential equation , finite element method , set (abstract data type) , programming language , politics , law , political science
Abstract An implicit unsteady, multiblock, multigrid, upwind solver including mesh deformation capability, and structured multiblock grid generator, are presented and applied to lifting rotors in both hover and forward flight. To allow the use of very fine meshes and, hence, better representation of the flow physics, a parallel version of the code has been developed. It is demonstrated that once the grid density is sufficient to capture enough turns of the tip vortices, hover exhibits oscillatory behaviour of the wake, even using a steady formulation. An unsteady simulation is then presented, and detailed analysis of the time‐accurate wake history is performed and compared to theoretical predictions. Forward flight simulations are also presented and, again, grid density effects on the wake formation investigated. Parallel performance of the code using up to 1024 CPU's is also presented. Copyright © 2006 John Wiley & Sons, Ltd.