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Numerical study of low pressure nuclear thermal rocketsThe flowfields and performance of low pressure nuclear thermal rockets, which use hydrogen as a propellant, are studied by solving the Navier-Stokes equations and the species equations. A finite-rate chemistry model is used in the species equations, and the turbulence is simulated by the Baldwin-Lomax turbulence model with a modified van Driest's damping constant. The calculated results for the chamber temperatures of 3200 K and 4000 K with a chamber pressure range of 0.1 atm to 6 atm are presented as contours, centerline variations, and exit profiles. The performance values from the present calculations, such as the vacuum specific impulse and thrust, are compared with those from the 1D, inviscid equilibrium and frozen flow code.
Document ID
19920071558
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kim, Suk C.
(Sverdrup Technology, Inc.; NASA, Lewis Research Center Cleveland, OH, United States)
Stubbs, Robert M.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 92-3815
Accession Number
92A54182
Funding Number(s)
CONTRACT_GRANT: NAS3-25266
Distribution Limits
Public
Copyright
Other

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