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A study of high speed flows in an aircraft transition ductThe study of circular-to-rectangular transition duct flows with and without inlet swirl is presented. A method was devised to create a swirling, solid body rotational flow with minimal associated disturbances. Details of the swirl generator design and construction are discussed. Coefficients based on velocities and total and static pressures measured in cross stream planes at four axial locations within the transition duct along with surface static pressures and surface oil film visualization are presented for both nonswirling and swirling incoming flows. A method was developed to acquire trace gas measurements within the transition duct at high flow velocities. Statistical methods are used to help interpret the trace gas results.
Document ID
19910016808
Acquisition Source
Legacy CDMS
Document Type
Thesis/Dissertation
Authors
Reichert, Bruce A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
E-6290
NASA-TM-104449
NAS 1.15:104449
Accession Number
91N26122
Funding Number(s)
PROJECT: RTOP 505-62-91
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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