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Numerical modeling of a vortex stabilized arcjet thrusterA numerical method to solve the equations governing a vortex stabilized arcjet thruster is being developed. The model will allow the effects of swirling flow and geometry on arcjet thruster performance to be determined. The propellant flow equations, i.e., the axisymmetric, thin layer, Navier-Stokes equations, are solved using a Gauss-Siedel line-relaxation procedure. An implicit FTCS method is used to solve the electromagnetic field equations. A grid generation scheme was developed for an arbitrary arcjet geometry. The model will allow the radial and axial components of velocity and current distributions to be determined from a region upstream of the cathode, through the constrictor, to the exit plane of the nozzle.
Document ID
19890059674
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Keith, Theo G., Jr.
(Toledo, University OH, United States)
Pawlas, Gary E.
(Toledo Univ. OH, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1989
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 89-2724
Accession Number
89A47045
Distribution Limits
Public
Copyright
Other

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