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Pressure recovery, drag, and subcritical stability characteristics of conical supersonic diffusers with boundary-layer removalA study of two 20 degrees half-angle, low mass-flow ratio conical supersonic inlets with cone boundary-layer bleed was made on a 16-inch ram-jet engine in the Lewis 8- by 6-foot supersonic wind tunnel. A greater stable subcritical range of operation was obtained with the bleed inlets than with the corresponding inlet without boundary-layer bleed. The drag added by the bleed system was small.
Document ID
19930094389
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Obey, Leonard T
Englert, Gerald W
Nussdorfer, Theodore J , Jr
Date Acquired
August 16, 2013
Publication Date
February 27, 1952
Report/Patent Number
NACA-RM-E51H29
Report Number: NACA-RM-E51H29
Accession Number
93R23308
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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