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Numerical investigation of unsteady flow development in a nozzle-duct configurationA computational approach has been used to resolve the transient phenomena caused by a rocket engine starting up and exhausting into a short duct. The results are obtained from the finite-difference Navier-Stokes, continuity, and energy equations for a single component gas. Using a recently developed numerical technique to account for the time-varying boundary conditions at the nozzle throat and the duct openings, the numerical simulation of the idealized ignition flow model has yielded some insight into the complex interactions between the wave patterns and the vortical flow. The present findings verify the hypothesis that a lateral expansion of the jetstream outside the nozzle will generate an over-pressure pulse on the duct wall if the jetstream is restricted within the nozzle by flow separation. The numerical simulations of this complex flow problem should be useful for improving simple correlation techniques used for engineering purposes.
Document ID
19830056869
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Li, C. P.
(NASA Johnson Space Center Houston, TX, United States)
Date Acquired
August 11, 2013
Publication Date
July 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 83-1714
Accession Number
83A38087
Distribution Limits
Public
Copyright
Other

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