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Investigation of effect of propulsion system installation and operation on aerodynamics of an airbreathing hypersonic airplane at Mach 0.3 to 1.2Results from an investigation of the effects of the operation of a combined turbojet/scramjet propulsion system on the longitudinal aerodynamic characteristics of a 1/60-scale hypersonic airbreathing launch vehicle configuration are presented. Decomposition products of hydrogen peroxide were used for simulation of the propulsion system exhaust.
Document ID
19770021149
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Cubbage, J. M. (NASA Langley Research Center Hampton, VA, United States)
Mercer, C. E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
July 1, 1977
Subject Category
Aerodynamics
Report/Patent Number
NASA-TN-D-8503
Report Number: NASA-TN-D-8503
Accession Number
77N28093
Funding Number(s)
PROJECT: RTOP 505-11-31-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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