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Application of FUN3D Solver for Aeroacoustics Simulation of a Nose Landing Gear ConfigurationNumerical simulations have been performed for a nose landing gear configuration corresponding to the experimental tests conducted in the Basic Aerodynamic Research Tunnel at NASA Langley Research Center. A widely used unstructured grid code, FUN3D, is examined for solving the unsteady flow field associated with this configuration. A series of successively finer unstructured grids has been generated to assess the effect of grid refinement. Solutions have been obtained on purely tetrahedral grids as well as mixed element grids using hybrid RANS/LES turbulence models. The agreement of FUN3D solutions with experimental data on the same size mesh is better on mixed element grids compared to pure tetrahedral grids, and in general improves with grid refinement.
Document ID
20110012467
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Vatsa, Veer N. (NASA Langley Research Center Hampton, VA, United States)
Lockard, David P. (NASA Langley Research Center Hampton, VA, United States)
Khorrami, Mehdi R. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 8, 2013
Publication Date
June 6, 2011
Subject Category
Aerodynamics
Report/Patent Number
NF1676L-11658
Meeting Information
Meeting: 17th AIAA/CEAS Aeroacoustics Conference
Location: Portland, OR
Country: United States
Start Date: June 6, 2011
End Date: June 8, 2011
Sponsors: National Oceanic and Atmospheric Administraion, American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 561581.02.08.07.18
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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