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Transonic Performance Characteristics of Several Jet Noise SuppressorsAn investigation of the transonic performance characteristics of several noise-suppressor configurations has been conducted in the Langley 16-foot transonic tunnel. The models were tested statically and over a Mach number range from 0.70 to 1.05 at an angle of attack of 0 deg. The primary jet total-pressure ratio was varied from 1.0 (jet off) to about 4.5. The effect of secondary air flow on the performance of two of the configurations was investigated. A hydrogen peroxide turbojet-engine simulator was used to supply the hot-jet exhaust. An 8-lobe afterbody with centerbody, short shroud, and secondary air had the highest thrust-minus-drag coefficients of the six noise-suppressor configurations tested. The 12-tube and 12-lobe afterbodies had the lowest internal losses. The presence of an ejector shroud partially shields the external pressure distribution of the 8-lobe after-body from the influence of the primary jet. A ring-airfoil shroud increased the static thrust of the annular nozzle but generally decreased the thrust minus drag at transonic Mach numbers.
Document ID
19980228155
Acquisition Source
Headquarters
Document Type
Other - NASA Technical Note (TN)
Authors
Schmeer, James W. (NASA Langley Research Center Hampton, VA United States)
Salters, Leland B., Jr. (NASA Langley Research Center Hampton, VA United States)
Cassetti, Marlowe D. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1960
Subject Category
Acoustics
Report/Patent Number
NASA-TN-D-388
L-850
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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