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Nozzle Modification Suppresses Flow TransientsProposal for steadying flow from rocket nozzle on Space Shuttle main engine could be applied to other large-area-ratio contoured nozzles. Oscillations and pulsations in boundary-layer flow would be reduced by flaring nozzle exit. Transient side loads on nozzle would be suppressed. Large pressure gradients and eddies that can lead to fluctuations are suppressed. Exact radius of curvature of corner would depend on shear-layer thickness.
Document ID
19810000061
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Rao, G. V. R. (Rockwell International Corp.)
Date Acquired
August 11, 2013
Publication Date
September 1, 1982
Publication Information
Publication: NASA Tech Briefs
Volume: 6
Issue: 1
ISSN: 0145-319X
Subject Category
Mechanics
Report/Patent Number
MFS-19567
ISSN: 0145-319X
Report Number: MFS-19567
Accession Number
81B10061
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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