Noise measurements from an ejector suppressor nozzle in the NASA Lewis 9- by 15-foot low speed wind tunnelAcoustic results are presented on nozzle test experiments conducted in the NASA Lewis 9 x 15-ft anechoic wind tunnel on a 'hypermix' nozzle concept, a two-dimensional lobed mixer nozzle followed by a short ejector section designed to promote rapid mixing of the nozzle flow with the flow induced by the ejector. Acoustic and aerodyanmic measurements were carried out to determine the amount of ejector pumping, the degree of mixing, and the noise reduction achieved. Spectra from various nozzle configurations were compared to show the effect of the nozzle geometry on nozzle-alone noise, the benefit of adding an ejector to the mixer nozzles, and the effect of the ejector geometry on ejector/suppressor noise level.
Document ID
19910027873
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Krejsa, Eugene A. (NASA Lewis Research Center Cleveland, OH, United States)
Cooper, Beth A. (NASA Lewis Research Center Cleveland, OH, United States)
Hall, David G. (NASA Lewis Research Center Cleveland, OH, United States)
Khavaran, Abbas (NASA Lewis Research Center; Sverdrup Technology, Inc. Brook Park, OH, United States)