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Suppressing Transient Side Loads in Supersonic NozzlesFins added to nozzle wall. Fins protrude from rocket nozzle wall at equal intervals about circumference. Inhibit circumferential growth of local flow separations, reducing sideways vibration of nozzle. Transientsuppressing fins helpful in rocket nozzles, jet engines, gas turbines, laser nozzles, flow diffusers, flow separators and other devices with supersonic flows.
Document ID
19830000379
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Wagner, W. R. (Rockwell International Corp)
Date Acquired
August 11, 2013
Publication Date
April 1, 1984
Publication Information
Publication: NASA Tech Briefs
Volume: 8
Issue: 1
ISSN: 0145-319X
Subject Category
Mechanics
Report/Patent Number
MFS-19769
Accession Number
83B10379
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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