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Navier-Stokes analysis of solid propellant rocket motor internal flowsA multidimensional implicit Navier-Stokes analysis that uses numerical solution of the ensemble-averaged Navier-Stokes equations in a nonorthogonal, body-fitted, cylindrical coordinate system has been applied to the simulation of the steady mean flow in solid propellant rocket motor chambers. The calculation procedure incorporates a two-equation (k-epsilon) turbulence model and utilizes a consistently split, linearized block-implicit algorithm for numerical solution of the governing equations. The code was validated by comparing computed results with the experimental data obtained in cylindrical-port cold-flow tests. The agreement between the computed and experimentally measured mean axial velocities is excellent. The axial location of transition to turbulent flow predicted by the two-equation (k-epsilon) turbulence model used in the computations also agrees well with the experimental data. Computations performed to simulate the axisymmetric flowfield in the vicinity of the aft field joint in the Space Shuttle solid rocket motor using 14,725 grid points show the presence of a region of reversed axial flow near the downstream edge of the slot.
Document ID
19900029308
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Sabnis, J. S.
(Scientific Research Associates, Inc. Glastonbury, CT, United States)
Gibeling, H. J.
(Scientific Research Associates, Inc. Glastonbury, CT, United States)
Mcdonald, H.
(Scientific Research Associates, Inc. Glastonbury, CT, United States)
Date Acquired
August 14, 2013
Publication Date
December 1, 1989
Publication Information
Publication: Journal of Propulsion and Power
Volume: 5
ISSN: 0748-4658
Subject Category
Fluid Mechanics And Heat Transfer
Accession Number
90A16363
Funding Number(s)
CONTRACT_GRANT: F04611-83-C-0003
CONTRACT_GRANT: NAS8-36185
Distribution Limits
Public
Copyright
Other

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