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Effect of hypersonic research engine installation on aerodynamic characteristics of 0.0667-scale model of X-15A-2 airplane at Mach numbers from 1.75 to 4.63Wind tunnel stability tests to determine effect of hypersonic research engine on aerodynamic characteristics of research aircraft
Document ID
19690029227
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Graves, E. B. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
August 1, 1969
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-1840
Report Number: NASA-TM-X-1840
Accession Number
69N38612
Funding Number(s)
CONTRACT_GRANT: 722-03-00-06-23
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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