NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Hybrid Wing Body Shielding Studies Using an Ultrasonic Configurable Fan Artificial Noise Source Generating Typical Turbofan ModesAn Ultrasonic Configurable Fan Artificial Noise Source (UCFANS) was designed, built, and tested in support of the NASA Langley Research Center's 14- by 22-ft wind tunnel test of the Hybrid Wing Body (HWB) full 3-D 5.8 percent scale model. The UCFANS is a 5.8 percent rapid prototype scale model of a high-bypass turbofan engine that can generate the tonal signature of proposed engines using artificial sources (no flow). The purpose of the test was to provide an estimate of the acoustic shielding benefits possible from mounting the engine on the upper surface of an HWB aircraft using the projected signature of the engine currently proposed for the HWB. The modal structures at the rating points were generated from inlet and exhaust nacelle configurations--a flat plate model was used as the shielding surface and vertical control surfaces with correct plan form shapes were also tested to determine their additional impact on shielding. Radiated acoustic data were acquired from a traversing linear array of 13 microphones, spanning 36 in. Two planes perpendicular, and two planes parallel, to the axis of the nacelle were acquired from the array sweep. In each plane the linear array traversed four sweeps, for a total span of 168 in. acquired. The resolution of the sweep is variable, so that points closer to the model are taken at a higher resolution. Contour plots of Sound Pressure Levels, and integrated Power Levels, from nacelle alone and shielded configurations are presented in this paper; as well as the in-duct mode power levels
Document ID
20140005372
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Sutliff, Daniel l.
(NASA Glenn Research Center Cleveland, OH, United States)
Brown, Clifford A.
(NASA Glenn Research Center Cleveland, OH, United States)
Walker, Bruce E.
(Channel Islands Acoustics Camarillo, CA, United States)
Date Acquired
May 9, 2014
Publication Date
April 1, 2014
Subject Category
Research And Support Facilities (Air)
Acoustics
Aircraft Propulsion And Power
Report/Patent Number
NASA/TM-2014-218119
AIAA Paper 2014-0256
E-18861
Meeting Information
Meeting: SciTech 2014
Location: Baltimore, MD
Country: United States
Start Date: January 13, 2014
End Date: January 17, 2014
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 699959.02.10.03.05
Distribution Limits
Public
Copyright
Public Use Permitted.
No Preview Available