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Navier-Stokes calculation of solid-propellant rocket motor internal flowfieldsA comprehensive numerical analysis has been carried out to study the detailed physical and chemical processes involved in the combustion of homogeneous propellant in a rocket motor. The formulation is based on the time-dependent full Navier-Stokes equations, with special attention devoted to the chemical reactions in both gas and condensed phases. The turbulence closure is achieved using both the Baldwin-Lomax algebraic model and a modified k-epsilon two-equation scheme with a low Reynolds number and near-wall treatment. The effects of variable thermodynamic and transport properties are also included. The system of governing equations are solved using a multi-stage Runge-Kutta shceme with the source terms treated implicitly. Preliminary results clearly demonstrate the presence of various combustion regimes in the vicinity of propellant surface. The effects of propellant combustion on the motor internal flowfields are investigated in detail.
Document ID
19890027612
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hsieh, Kwang-Chung
(NASA Lewis Research Center; Sverdrup Technology, Inc. Cleveland, OH, United States)
Yang, Vigor
(NASA Lewis Research Center Cleveland, OH, United States)
Tseng, Jesse I. S.
(Pennsylvania State University University Park, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1988
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 88-3182
Accession Number
89A14983
Funding Number(s)
CONTRACT_GRANT: F04611-86-K-0082
Distribution Limits
Public
Copyright
Other

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