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Mach 4 and Mach 8 axisymmetric nozzles for a high-enthalpy shock tunnelThe performance of two axisymmetric nozzles which were designed to produce uniform, parallel flow with nominal Mach numbers of 4 and 8 is examined. A free-piston-driven shock tube was used to supply the nozzle with high-temperature, high-pressure test gas. The inviscid design procedure treated the nozzle expansion in two stages. Close to the nozzle throat, the nozzle wall was specified as conical and the gas flow was treated as a quasi-one-dimensional chemically-reacting flow. At the end of the conical expansion, the gas was assumed to be calorically perfect, and a contoured wall was designed (using method of characteristics) to convert the source flow into a uniform and parallel flow at the end of the nozzle. Performance was assessed by measuring Pitot pressures across the exit plane of the nozzles and, over the range of operating conditions examined, the nozzles produced satisfactory test flows. However, there were flow disturbances in the Mach 8 nozzle flow that persisted for significant times after flow initiation.
Document ID
19920034044
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Jacobs, P. A.
(NASA Langley Research Center; ICASE Hampton, VA, United States)
Stalker, R. J.
(Queensland, University St. Lucia, Australia)
Date Acquired
August 15, 2013
Publication Date
November 1, 1991
Publication Information
Publication: Aeronautical Journal
Volume: 95
ISSN: 0001-9240
Subject Category
Aerodynamics
Accession Number
92A16668
Funding Number(s)
CONTRACT_GRANT: NAS1-18605
CONTRACT_GRANT: NAGW-674
Distribution Limits
Public
Copyright
Other

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