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Mixing effectiveness test of an exhaust gas mixer in a high bypass turbofan at altitudeThermal mixing effectiveness characteristics of an eighteen lobe, scalloped and unscalloped, partial, forced mixer were measured in a high-bypass turbofan engine. Data were also obtained without the mixer installed, i.e., free mixing. Tests were conducted at four combinations of simulated flight conditions from 0.3 to 0.8 Mach number and from 6,096 meters (20,000 ft) to 13,715 m (45,000 ft) altitude, mixing chamber lengths of L/D=0.52 and 0.65 were tested. For this range of test conditions and mixer configurations, the forced mixing effectiveness varied from 59 to 68 percent. Values of mixing effectiveness and total pressure loss were calculated from temperature and pressure data obtained at the mixer inlet and exhaust nozzle exit.
Document ID
19810018557
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cullom, R. R.
(NASA Lewis Research Center Cleveland, OH, United States)
Bobula, G. A.
(NASA Lewis Research Center Cleveland, OH, United States)
Burkardt, L. A.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1981
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-938
NASA-TM-82663
AVRADCOM-TR-81-C-24
Report Number: E-938
Report Number: NASA-TM-82663
Report Number: AVRADCOM-TR-81-C-24
Meeting Information
Meeting: Joint Propulsion Conf.
Location: Colorado Springs, CO
Country: United States
Start Date: July 27, 1981
End Date: July 29, 1981
Sponsors: SAE, AIAA, ASME
Accession Number
81N27095
Funding Number(s)
PROJECT: RTOP 505-23-6A
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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