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A Full Navier-Stokes Analysis of Subsonic Diffuser of a Bifurcated 70/30 Supersonic Inlet for High Speed Civil Transport ApplicationA full Navier-Stokes analysis was performed to evaluate the performance of the subsonic diffuser of a NASA Lewis Research Center 70/30 mixed-compression bifurcated supersonic inlet for high speed civil transport application. The PARC3D code was used in the present study. The computations were also performed when approximately 2.5 percent of the engine mass flow was allowed to bypass through the engine bypass doors. The computational results were compared with the available experimental data which consisted of detailed Mach number and total pressure distribution along the entire length of the subsonic diffuser. The total pressure recovery, flow distortion, and crossflow velocity at the engine face were also calculated. The computed surface ramp and cowl pressure distributions were compared with experiments. Overall, the computational results compared well with experimental data. The present CFD analysis demonstrated that the bypass flow improves the total pressure recovery and lessens flow distortions at the engine face.
Document ID
Acquisition Source
Document Type
Technical Memorandum (TM)
Kapoor, Kamlesh
(NASA Lewis Research Center Cleveland, OH, United States)
Anderson, Bernhard H.
(NASA Lewis Research Center Cleveland, OH, United States)
Shaw, Robert J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1994
Subject Category
Report/Patent Number
NAS 1.15:106637
Accession Number
Funding Number(s)
PROJECT: RTOP 537-02-23
Distribution Limits
Work of the US Gov. Public Use Permitted.
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