|
Accession Number
|
N20120010288
|
|
Title
|
Aeroacoustic Simulation of a Nose Landing Gear in an Open Jet Facility Using FUN3D.
|
|
Publication Date
|
Jun 2012
|
|
Media Count
|
18p
|
|
Personal Author
|
D. P. Lockhard J. R. Carlson M. R. Khorrami V. N. Vatsa
|
|
Abstract
|
Numerical simulations have been performed for a partially-dressed, cavity-closed nose landing gear configuration that was tested in NASA Langley s closed-wall Basic Aerodynamic Research Tunnel (BART) and in the University of Florida s open-jet acoustic facility known as UFAFF. The unstructured-grid flow solver, FUN3D, developed at NASA Langley Research center is used to compute the unsteady flow field for this configuration. A hybrid Reynolds-averaged Navier-Stokes/large eddy simulation (RANS/LES) turbulence model is used for these computations. Time-averaged and instantaneous solutions compare favorably with the measured data. Unsteady flowfield data obtained from the FUN3D code are used as input to a Ffowcs Williams-Hawkings noise propagation code to compute the sound pressure levels at microphones placed in the farfield. Significant improvement in predicted noise levels is obtained when the flowfield data from the open jet UFAFF simulations is used as compared to the case using flowfield data from the closed-wall BART configuration.
|
|
Keywords
|
Computational aeroacoustics
Computational fluid dynamics
Dynamic models
Ffowcs williams-hawkings equation
Flow noise
Landing gear
Large eddy simulation
Microphones
Navier-stokes equation
Noise intensity
Noise prediction(Aircraft)
Noise propagation
Reynolds averaging
Turbulence models
Unsteady flow
Unstructured grids(Mathematics)
Wind tunnel tests
|
|
|
Source Agency
|
National Aeronautics and Space Administration
|
|
NTIS Subject Category
|
46A - Acoustics
51F - Test Facilities & Equipment
|
|
Corporate Author
|
National Aeronautics and Space Administration, Hampton, VA. Langley Research Center.
|
|
Document Type
|
Conference proceedings
|
|
Title Note
|
N/A
|
|
NTIS Issue Number
|
1226
|
|
Contract Number
|
N/A
|
