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Study of compressible flow through a rectangular-to-semiannular transition ductDetailed flow field measurements are presented for compressible flow through a diffusing rectangular-to-semiannular transition duct. Comparisons are made with published computational results for flow through the duct. Three-dimensional velocity vectors and total pressures were measured at the exit plane of the diffuser model. The inlet flow was also measured. These measurements are made using calibrated five-hole probes. Surface oil flow visualization and surface static pressure data were also taken. The study was conducted with an inlet Mach number of 0.786. The diffuser Reynolds based on the inlet centerline velocity and the exit diameter of the diffuser was 3,200,000. Comparison of the measured data with previously published computational results are made. Data demonstrating the ability of vortex generators to reduce flow separation and circumferential distortion is also presented.
Document ID
19950017972
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Foster, Jeffry (Iowa State Univ. of Science and Technology Ames, IA, United States)
Okiishi, Theodore H. (Iowa State Univ. of Science and Technology Ames, IA, United States)
Wendt, Bruce J. (Modern Technologies Corp. Middleburg Heights, OH., United States)
Reichert, Bruce A. (Kansas State Univ. Manhattan, KS., United States)
Date Acquired
September 6, 2013
Publication Date
April 1, 1995
Publication Information
Publisher: NASA
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-4660
E-9582
NAS 1.26:4660
Accession Number
95N24392
Funding Number(s)
CONTRACT_GRANT: NAG3-1561
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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