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Modeling flow at the nozzle of a solid rocket motorThe mechanical behavior of a rocket motor internal flow field results in a system of nonlinear partial differential equations which can be solved numerically. The accuracy and the convergence of the solution of the system of equations depends largely on how precisely the sharp gradients can be resolved. An adaptive grid generation scheme is incorporated into the computer algorithm to enhance the capability of numerical modeling. With this scheme, the grid is refined as the solution evolves. This scheme significantly improves the methodology of solving flow problems in rocket nozzle by putting the refinement part of grid generation into the computer algorithm.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Chow, Alan S.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Jin, Kang-Ren
(Mississippi State University Mississippi State, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1991
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 91-2432
Accession Number
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