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Experimental Investigation of the Performance of a Mach-2.7 Two-dimensional Bifurcated Duct Inlet with 30 Percent Internal ContractionAn experimental study was conducted to determine the performance of a two-dimensional, mixed-compression bifurcated duct inlet system designed for a free-stream Mach number of 2.7. Thirty percent of the supersonic area contraction occurred internally. A movable ramp was used to vary the contraction ratio for off-design operation. Boundary layer bleed regions were located on the cowl, centerbody, and sidewall surfaces. There were also provisions for vortex generators on the cowl and centerbody of the subsonic diffuser. Data were obtained over the Mach number range of 2.0 to 2.8 and at angles of yaw from 0 deg. to the maximum value prior to inlet un-start. The test at Mach 2.8 was to obtain data for an over- speed condition. The Reynolds number varied from 2.5 to 2.3 million/ft for Mach numbers above 2.5. At Mach numbers of 2.5 and lower, the Reynolds number was set at 2.5 million/ft. Bleed patterns, vortex generator patterns, and ramp position were varied, and three inlet configurations were selected for more extensive study. Two of these configurations had self-starting capability. The self-starting configuration that was developed produced 89 percent total pressure recovery at the compressor face station with 6.8 percent total bleed. The compressor face distortion was about 16 percent. Vortex generators were extremely effective in re-distributing flow but were not as effective in reducing distortion. Excellent flow symmetry was achieved between the separated halves of the inlet, and twin-duct instability was not observed. The ramp tip shock was steeper than expected. This caused the cowl lip shock to be reflected from the ramp instead of being cancelled at the shoulder. However, peak recovery at the throat was still obtained with the ramp near the design position.
Document ID
19960026650
Acquisition Source
Headquarters
Document Type
Technical Memorandum (TM)
Authors
Wasserbauer, J. F.
(NASA Lewis Research Center Cleveland,OH United States)
Meleason, E. T.
(NASA Lewis Research Center Cleveland,OH United States)
Burstadt, P. L.
(NASA Lewis Research Center Cleveland,OH United States)
Date Acquired
September 6, 2013
Publication Date
May 1, 1996
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-9099
NASA-TM-106728
NAS 1.16:106728
Accession Number
96N28217
Funding Number(s)
PROJECT: RTOP 537-02-23
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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