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Mach 4 and Mach 8 axisymmetric nozzles for a high-enthalpy shock tunnel

Published online by Cambridge University Press:  04 July 2016

P. A. Jacobs  and
R. J. Stalker
P. A. Jacobs
Affiliation:
Institute for Computer Applications in Science and Engineering, NASA Langley Research Center, USA
R. J. Stalker
Affiliation:
Department of Mechanical Engineering, University of Queensland, Australia
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Abstract

This study examines the performance of two axisymmetric nozzles which were designed to produce uniform, parallel flow with nominal Mach numbers of 4 and 8. 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.

Type
Research Article
Information
The Aeronautical Journal , Volume 95 , Issue 949 , November 1991 , pp. 324 - 334
Copyright
Copyright © Royal Aeronautical Society 1991 

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Footnotes

*

Current address: Department of Mechanical Engineering, University of Queensland.

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