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Exhaust environment measurements of a turbofan engine equipped with an afterburner and 2D nozzleA test to measure the acoustic noise and static pressure environment on a structure exposed to engine exhaust flow was conducted at the NASA Lewis Research Center Propulsion Systems Laboratory by using an F100 derivative engine with a two-dimensional convergent-divergent (2D/CD) non-flight-weight demonstrator nozzle. A highly instrumented, water cooled flat panel was placed behind the 2D/CD nozzle, and tests were conducted at simulated Mach/altitude flight conditions with the engine at military or maximum-afterburner power setting. The panel instrumentation consisted of acoustic pressure microphones, thermocouples, and static-pressure pickups. Measurements indicated that the exhaust environment may excite structural resonances up to 10,000 HZ and that overall sound pressure levels decrease with increasing altitude.
Document ID
19900012444
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Brase, L. O. (McDonnell Aircraft Co. Saint Louis, MO, United States)
Date Acquired
September 6, 2013
Publication Date
May 1, 1990
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-4289
NAS 1.26:4289
E-5302
Accession Number
90N21760
Funding Number(s)
PROJECT: RTOP 505-62-91
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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