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Performance of vortex generators in a Mach 2.5 low-bleed full scale 45-percent-internal-contraction axisymmetric inletSteady-state and dynamic flow characteristics associated with two sets of vortex generators having different mixing criteria were determined. The inlet performance with and without these vortex generators is presented. The vortex generators were successful in eliminating separation, increasing area-weighted total pressure recovery, and decreasing distortion. Transmission times obtained from cross-correlations of the wall static pressures and the diffuser exit total pressure showed no effect of the upstream flow characteristics on the diffuser exit pressures when generators were used. Without generators, separation occurred and the upstream pressure characteristics had immediate effects on the diffuser exit pressure characteristics.
Document ID
19750012263
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Neumann, H. E.
(NASA Lewis Research Center Cleveland, OH, United States)
Wasserbauer, J. F.
(NASA Lewis Research Center Cleveland, OH, United States)
Shaw, R. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1975
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TM-X-3195
E-8117
Report Number: NASA-TM-X-3195
Report Number: E-8117
Accession Number
75N20335
Funding Number(s)
PROJECT: RTOP 505-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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