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Investigation of the Air-flow-regulation Characteristics of a Translating-spike Inlet with Two Oblique Shocks from Mach 1.6 to 2.0Translating spike inlet air flow regulation characteristics from transonic to supersonic speeds at zero angle of attack
Document ID
19660010449
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Nettles, J. C. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
July 24, 1956
Subject Category
Aerodynamics
Report/Patent Number
NACA-RM-E56D23B
Accession Number
66N19738
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
AIR INLET
SUPERSONIC SPEED
FLOW REGULATOR
TRANSONIC SPEED
ZERO ANGLE OF ATTACK

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