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Slat Noise Predictions Using Higher-Order Finite-Difference Methods on Overset GridsComputational aeroacoustic simulations using the structured overset grid approach and higher-order finite difference methods within the Launch Ascent and Vehicle Aerodynamics (LAVA) solver framework are presented for slat noise predictions. The simulations are part of a collaborative study comparing noise generation mechanisms between a conventional slat and a Krueger leading edge flap. Simulation results are compared with experimental data acquired during an aeroacoustic test in the NASA Langley Quiet Flow Facility. Details of the structured overset grid, numerical discretization, and turbulence model are provided.
Document ID
20170000217
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Housman, Jeffrey A. (NASA Ames Research Center Moffett Field, CA United States)
Kiris, Cetin (NASA Ames Research Center Moffett Field, CA United States)
Date Acquired
January 4, 2017
Publication Date
May 30, 2016
Subject Category
Aeronautics (General)
Acoustics
Report/Patent Number
ARC-E-DAA-TN32468
Meeting Information
Meeting: AIAA/CEAS Aeroacoustics Conference
Location: Lyon
Country: France
Start Date: May 30, 2016
End Date: June 1, 2016
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
Overset Grids
Prediction
Higher-Order

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