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Forward velocity effects on under-the-wing externally blown flap noiseNoise tests were conducted with small-scale models of externally blown-flap powered-lift systems that were subjected to simulated takeoff and landing free-stream velocities by placing the nozzle-wing models in a free jet. The nozzle configurations consisted of a conical and an 8-tube mixer nozzle. The results show that the free-stream velocity attenuates the noise from the various configurations, with the amount of attenuation depending on the flap setting. More attenuation was obtained with a flap setting of 20 degrees than with a flap setting of 60 degrees. The dynamic effect on the total attenuation caused by aircraft motion is also discussed.
Document ID
19750007581
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Goodykoontz, J. (NASA Lewis Research Center Cleveland, OH, United States)
Vonglahn, U. (NASA Lewis Research Center Cleveland, OH, United States)
Dorsch, R. G. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1975
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-8235
NASA-TM-X-71656
Report Number: E-8235
Report Number: NASA-TM-X-71656
Meeting Information
Meeting: 2d Aero-Acoustics Specialists Conf.
Location: Hampton, VA
Country: United States
Start Date: March 24, 1975
End Date: March 26, 1975
Sponsors: AIAA
Accession Number
75N15653
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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