Thrust performance of isolated plug nozzles with two types of 40-spoke noise suppressor at Mach numbers from 0 to 0.45 /

Plug nozzles with two types of 40-spoke noise suppressor were tested at free-stream Mach numbers from 0 to 0.45 and over a range of nozzle pressure ratios from 1.5 to 4.0. In addition, an unsuppressed plug nozzle and a Supersonic Tunnel Association nozzle were also tested to provide baseline levels...

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Bibliographic Details
Main Author:	Harrington, Douglas E
Corporate Author:	Lewis Research Center
Other Authors:	Schloemar, James J
Format:	Government Document Book
Language:	English
Published:	Washington, D.C. : Springfield, Va. : National Aeronautics and Space Administration ; For sale by the National Technical Information Service [distributor], 1974
Series:	NASA technical memorandum X-2951
Subjects:	Airplanes > Motors > Thrust Airplanes > Turbojet engines > Mufflers Jet nozzles > Testing Jet aircraft noise Noise reduction Performance tests Plug nozzles Supersonic wind tunnels Thrust measurement Turbojet engines

by Harrington, Douglas E
Published 1974

Government Document Book

Thrust performance of isolated plug nozzles with two types of 40-spoke noise suppressor at Mach numbers from 0 to 0.45 /

by Harrington, Douglas E
Published 1974

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Thrust performance of isolated plug nozzles with two types of 40-spoke noise suppressor at Mach numbers from 0 to 0.45 /

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