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Acoustics of a Supersonic Mach 1.4 Axisymmetric Spike InletAn inlet for a supersonic commercial aircraft is analyzed for noise radiation in low-speed configuration, with auxiliary inlet open. Duct mode amplitudes generated by the fan are determined by post-processing a URANS simulation and become a boundary condition to the inlet. Far-field sound is modeled using commercial acoustics finite element software. The effect of inlet geometry and acoustic liners is simulated and discussed. Absolute levels for inlet tone noise are predicted.
Document ID
20230006439
Acquisition Source
Glenn Research Center
Document Type
Presentation
Authors
David B Stephens (Glenn Research Center Cleveland, Ohio, United States)
Edmane Envia (Glenn Research Center Cleveland, Ohio, United States)
Date Acquired
April 26, 2023
Publication Date
June 12, 2023
Subject Category
Acoustics
Meeting Information
Meeting: AIAA AVIATION Forum and Exposition
Location: San Diego, CA
Country: US
Start Date: June 12, 2023
End Date: June 16, 2023
Sponsors: American Institute of Aeronautics and Astronautics
Funding Number(s)
WBS: 110076.02.03.04.40.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Technical Review
Single Expert
Keywords
Supersonics
Acoustics
Turbofan

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