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Perceived Noise Analysis for Offset Jets Applied to Commercial Supersonic AircraftA systems analysis was performed with experimental jet noise data, engine/aircraft performance codes and aircraft noise prediction codes to assess takeoff noise levels and mission range for conceptual supersonic commercial aircraft. A parametric study was done to identify viable engine cycles that meet NASA's N+2 goals for noise and performance. Model scale data from offset jets were used as input to the aircraft noise prediction code to determine the expected sound levels for the lateral certification point where jet noise dominates over all other noise sources. The noise predictions were used to determine the optimal orientation of the offset nozzles to minimize the noise at the lateral microphone location. An alternative takeoff procedure called "programmed lapse rate" was evaluated for noise reduction benefits. Results show there are two types of engines that provide acceptable mission range performance; one is a conventional mixed-flow turbofan and the other is a three-stream variable-cycle engine. Separate flow offset nozzles reduce the noise directed toward the thicker side of the outer flow stream, but have less benefit as the core nozzle pressure ratio is reduced. At the systems level for a three-engine N+2 aircraft with full throttle takeoff, there is a 1.4 EPNdB margin to Chapter 3 noise regulations predicted for the lateral certification point (assuming jet noise dominates). With a 10% reduction in thrust just after clearing the runway, the margin increases to 5.5 EPNdB. Margins to Chapter 4 and Chapter 14 levels will depend on the cumulative split between the three certification points, but it appears that low specific thrust engines with a 10% reduction in thrust (programmed lapse rate) can come close to meeting Chapter 14 noise levels. Further noise reduction is possible with engine oversizing and derated takeoff, but more detailed mission studies are needed to investigate the range impacts as well as the practical limits for safety and takeoff regulations.
Document ID
20160004680
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Huff, Dennis L.
(NASA Glenn Research Center Cleveland, OH United States)
Henderson, Brenda S.
(NASA Glenn Research Center Cleveland, OH United States)
Berton, Jeffrey J.
(NASA Glenn Research Center Cleveland, OH United States)
Seidel, Jonathan A.
(NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
April 6, 2016
Publication Date
January 4, 2016
Subject Category
Astronautics (General)
Acoustics
Report/Patent Number
GRC-E-DAA-TN28452
Meeting Information
Meeting: AIAA SciTech 2016 Conference
Location: San Diego, CA
Country: United States
Start Date: January 4, 2016
End Date: January 8, 2016
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 110076.02.03.04.40.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
Turbofans
Jet Noise
Acoustic
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