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Forward slanted slot throat stability bypass to increase the stable airflow range of a Mach 2.5 inlet with 60 percent internal contractionThe results of an experimental investigation to increase the stable airflow operating range of a supersonic mixed-compression inlet are presented. Two forward-slanted slot stability-bypass entrance configurations were tested. In terms of diffuser-exit corrected airflow, a large inlet stable airflow range of 18.5 percent was obtained with the superior configuration if a constant pressure was maintained in the bypass plenum. Limited unstart angle-of-attack data are presented.
Document ID
19740014514
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Shaw, R. J. (NASA Lewis Research Center Cleveland, OH, United States)
Mitchell, G. A. (NASA Lewis Research Center Cleveland, OH, United States)
Sanders, B. W. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
May 1, 1974
Subject Category
Aerodynamics
Report/Patent Number
E-7706
NASA-TM-X-2973
Accession Number
74N22627
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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