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Hypergolic bipropellant spray combustion and flow modelling in rocket enginesA predictive tool for hypergolic bipropellant spray combustion and flow evolution in small rocket combustion chambers is described. It encompasses a computational technique for the gas-phase governing equations, a discrete particle method for liquid bipropellant sprays, and constitutive models for combustion chemistry, interphase exchanges, and unlike impinging hypergolic spray interactions. Emphasis is placed on the phenomenological modeling of the hypergolic liquid bipropellant gasification processes. Sample computations with the N2H4-N2O4 propellant system are given in order to show some of the capabilities and inadequacies of this tool.
Document ID
19900055702
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Larosiliere, Louis M.
(Tennessee Univ. Space Inst. Tullahoma, TN, United States)
Litchford, Ron J.
(Tennessee Univ. Space Inst. Tullahoma, TN, United States)
Jeng, San-Mou
(Tennessee, University Tullahoma, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1990
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 90-2238
Accession Number
90A42757
Funding Number(s)
CONTRACT_GRANT: NAGW-1195
Distribution Limits
Public
Copyright
Other

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