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Pressure distributions for a rectangular supersonic inlet at subsonic speedsPressure distribution data are provided for a supersonic rectangular inlet at subsonic speeds. Variations in cowl and ramp geometry as well as sideplate sweep were investigated. Tests were made in the Langley 16-foot transonic tunnel and the Langley high speed 7- by 10-foot tunnel for Mach numbers of 0.6, 0.7, and 0.8. Angles of attack investigated were 0 deg, 4 deg, and 8 deg for a range of mass flow ratios.
Document ID
19760009987
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Fuller, D. E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
February 1, 1976
Subject Category
Aerodynamics
Report/Patent Number
L-10424
NASA-TM-X-3305
Report Number: L-10424
Report Number: NASA-TM-X-3305
Accession Number
76N17075
Funding Number(s)
PROJECT: RTOP 505-11-21-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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