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Numerical simulation of flows in curved diffusers with cross-sectional transitioning using a three-dimensional viscous analysisA three dimensional analysis for fully viscous, subsonic, compressible flow is evaluated. An approximate form of the Navier Stokes equations is solved by an implicit spatial marching technique. Calculations were made for flow in a circular S duct and in the F 16 inlet duct. The computed total pressure contours and secondary flow velocity vectors are presented. Qualitative comparisons with experiment are shown for both ducts. The analysis is used to show how the cross section transitioning in the F 16 inlet suppresses the development of a secondary flow vortex.
Document ID
19810006724
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Towne, C. E. (NASA Lewis Research Center Cleveland, OH, United States)
Anderson, B. H. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1981
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-TM-81672
E-696
Report Number: NASA-TM-81672
Report Number: E-696
Meeting Information
Meeting: Aerospace Sci. Meeting,
Location: St. Louis, MO
Country: United States
Start Date: January 12, 1981
End Date: January 15, 1981
Sponsors: AIAA
Accession Number
81N15239
Funding Number(s)
PROJECT: RTOP 505-32-12
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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