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PERFORMANCE OF AN INLET HAVING A VARIABLE-ANGLE TWO-DIMENSIONAL COMPRESSION SURFACE AND A FIXED-GEOMETRY SUBSONIC DIFFUSER FOR APPLICATION TO REDUCED ENGINE ROTATIVE SPEEDS- MACH NUMBERS 0.66, 1.5, 1.7, AND 2.0Air inlet for turbojet engines having variable angle two-dimensional compression surface and fixed-geometry subsonic diffuser
Document ID
19630003996
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Allen, J. L. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 1, 2013
Publication Date
January 30, 1958
Subject Category
Aircraft
Report/Patent Number
NACA-RM-E57J02
Accession Number
63N13872
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
TURBOJET ENGINE
AIR INLET

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