NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Numerical analysis of bipropellant combustion in liquid thrust chambers by an Eulerian-Eulerian approachThe liquid thrust chambers performance (LTCP) code is used for parametric studies of flow and combustion in liquid rocket engines. Multiphase flow equations are solved in an Eulerian-Eulerian framework, and multistep finite rate chemistry is incorporated. The discretization scheme is fully implicit and is based on the total variation diminishing (TVD) scheme, which is accurate, robust, very efficient and capable of handling steep gradients and stiff chemistry. Effects of injection velocity and chamber size have been considered, and the effect of group combustion on the evaporation rate has been studied for a dense spray.
Document ID
19920071515
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dang, A. L.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Navaz, H. K.
(Physical Research, Inc. Irvine, CA, United States)
Rangel, R. H.
(California, University Irvine, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 92-3735
Accession Number
92A54139
Funding Number(s)
CONTRACT_GRANT: NAS8-38798
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available