NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Fluidic Actuation for Aeropropulsive Acoustic ImprovementsExperiments were performed in NASAs SW-2 cascade facility to compare three trailing edge actuation concepts to a 3D airfoil section with no trailing edge treatment. At a Reynolds number of 105, trailing edge pulsed ejection using fluidic oscillator devices was shown to fill the momentum deficit in the wake more uniformly than other actuators tested, with expected benefits for tonal noise in engine fans. Furthermore, pulsed ejection was found to alter the acoustic signature of the wake to reduce broadband noise. In some locations in the wake, spectral components of velocity were found to be reduced by 2 to 5 dB across nearly all frequencies. Trailing edge pulsed ejection is established as a feasible concept to reduce both tonal and broadband noise emissions from aircraft engines.
Document ID
20180003526
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Stone, Mark (Princeton Univ. Princeton, NJ, United States)
Shyam, Vikram (NASA Glenn Research Center Cleveland, OH, United States)
Poinsatte, Philip E. (NASA Glenn Research Center Cleveland, OH, United States)
Thurman, Douglas R. (NASA Glenn Research Center Cleveland, OH, United States)
Raghu, Surya (Advanced Fluidics, LLC Columbia, MD, United States)
Date Acquired
June 13, 2018
Publication Date
June 1, 2018
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
GRC-E-DAA-TN46196
E-19533
NASA/TM-2018-219776
Funding Number(s)
WBS: WBS 081876.01.03.01
Distribution Limits
Public
Copyright
Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available