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Rocket nozzle lip flow by direct simulation Monte Carlo methodThe flow in the immediate vicinity of a rocket nozzle lip has been analyzed, and the results are presented. A rapid change in gas composition is observed in the flow around the lip depending principally on species molecular mass and local flow angle. The divergence of axial and radial temperatures indicating breakdown of translational equilibrium is observed in the results.
Document ID
19850055490
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hueser, J. E. (Old Dominion Univ. Norfolk, VA, United States)
Brock, F. J. (Old Dominion University Norfolk, VA, United States)
Melfi, L. T., Jr. (NASA Langley Research Center Space Systems Div., Hampton, VA, United States)
Bird, G. A. (Sydney, University Sydney, Australia)
Date Acquired
August 12, 2013
Publication Date
June 1, 1985
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 85-0995
Accession Number
85A37641
Distribution Limits
Public
Copyright
Other

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