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Measured and calculated flow conditions on the forward fuselage of the X-15 airplane and model at Mach numbers from 3.0 to 8.0Measured and calculated flow conditions on forward fuselage of X-15 plane and model at Mach numbers from 3.0 to 8.0
Document ID
19660017559
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Palitz, M. (NASA Flight Research Center Edwards, CA, United States)
Date Acquired
September 2, 2013
Publication Date
June 1, 1966
Subject Category
Aircraft
Report/Patent Number
NASA-TN-D-3447
Report Number: NASA-TN-D-3447
Accession Number
66N26849
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
FUSELAGE
MACH NUMBER
X-15 AIRCRAFT
SUPERSONIC FLOW
HYPERSONIC FLOW

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