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Mean Flow Boundary Conditions for Computational AeroacousticsIn this work, a new type of boundary condition for time-accurate Computational Aeroacoustics solvers is described. This boundary condition is designed to complement the existing nonreflective boundary conditions while ensuring that the correct mean flow conditions are maintained throughout the flow calculation. Results are shown for a loaded 2D cascade, started with various initial conditions.
Document ID
20030112851
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
R Hixon (University of Toledo Toledo, United States)
M Nallasamy (QSS Group Fairfax, Virginia, United States)
S Sawyer (University of Akron Akron, United States)
R Dyson (Glenn Research Center Cleveland, United States)
Date Acquired
September 7, 2013
Publication Date
May 12, 2003
Publication Information
Publication: 9th AIAA/CEAS Aeroacoustics Conference and Exhibit
Publisher: American Institute of Aeronautics and Astronautics
e-ISBN: 9781624101021
DOI: 10.2514/6.2003-3299
Subject Category
Acoustics
Fluid Mechanics and Thermodynamics
Report/Patent Number
AIAA-2003-3299
Meeting Information
Meeting: 9th AIAA/CEAS Aeroacoustics Conference and Exhibit
Location: Hilton Head, SC
Country: US
Start Date: May 12, 2003
End Date: May 14, 2003
Sponsors: Council of European Aerospace Societies, American Institute of Aeronautics and Astronautics
Funding Number(s)
WBS: 22-781-30-11
Distribution Limits
Public
Copyright
Portions of document may include copyright protected material.
Technical Review
NASA Technical Management
Keywords
Static Pressure
Stagnation Temperature
NASA Glenn Research Center
Euler Equations
Flow Conditions
Computational Aeroacoustics

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