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Development of acoustically lined ejector technology for multitube jet noise suppressor nozzles by model and engine tests over a wide range of jet pressure ratios and temperaturesAn experimental program comprising model nozzle and full-scale engine tests was undertaken to acquire parametric data for acoustically lined ejectors applied to primary jet noise suppression. Ejector lining design technology and acoustical scaling of lined ejector configurations were the major objectives. Ground static tests were run with a J-75 turbojet engine fitted with a 37-tube, area ratio 3.3 suppressor nozzle and two lengths of ejector shroud (L/D = 1 and 2). Seven ejector lining configurations were tested over the engine pressure ratio range of 1.40 to 2.40 with corresponding jet velocities between 305 and 610 M/sec. One-fourth scale model nozzles were tested over a pressure ratio range of 1.40 to 4.0 with jet total temperatures between ambient and 1088 K. Scaling of multielement nozzle ejector configurations was also studied using a single element of the nozzle array with identical ejector lengths and lining materials. Acoustic far field and near field data together with nozzle thrust performance and jet aerodynamic flow profiles are presented.
Document ID
19740014526
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Atvars, J.
(Boeing Commercial Airplane Co. Seattle, WA, United States)
Paynter, G. C.
(Boeing Commercial Airplane Co. Seattle, WA, United States)
Walker, D. Q.
(Boeing Commercial Airplane Co. Seattle, WA, United States)
Wintermeyer, C. F.
(Boeing Commercial Airplane Co. Seattle, WA, United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1974
Publication Information
Publisher: NASA
Subject Category
Aircraft
Report/Patent Number
NASA-CR-2382
D6-60226
Accession Number
74N22639
Funding Number(s)
CONTRACT_GRANT: NAS3-15570
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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