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A study of forced flow separation in rocket nozzleThe characteristics of flow profile in a rocket nozzle during the start transient were investigated as well as possibilities of reducing the side-load thrust by sticking trip wires in the nozzle. To simplify the geometry of flow configuration around the trip wire, it was assumed that the flow is passing through square steps instead of round wires. Since a purely analytic solution is not available, a series of semiempirical solutions was proposed.
Document ID
19740024633
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Chiou, J. N. (Alabama Univ. Huntsville, AL, United States)
Hung, R. J. (Alabama Univ. Huntsville, AL, United States)
Date Acquired
September 3, 2013
Publication Date
July 1, 1974
Subject Category
Fluid Mechanics
Report/Patent Number
NASA-CR-120422
Report Number: NASA-CR-120422
Accession Number
74N32746
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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