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Development of Detonation Modeling Capabilities for Rocket Test Facilities: Hydrogen-Oxygen-Nitrogen MixturesThe objective of the presented work was to develop validated computational fluid dynamics (CFD) based methodologies for predicting propellant detonations and their associated blast environments. Applications of interest were scenarios relevant to rocket propulsion test and launch facilities. All model development was conducted within the framework of the Loci/CHEM CFD tool due to its reliability and robustness in predicting high-speed combusting flow-fields associated with rocket engines and plumes. During the course of the project, verification and validation studies were completed for hydrogen-fueled detonation phenomena such as shock-induced combustion, confined detonation waves, vapor cloud explosions, and deflagration-to-detonation transition (DDT) processes. The DDT validation cases included predicting flame acceleration mechanisms associated with turbulent flame-jets and flow-obstacles. Excellent comparison between test data and model predictions were observed. The proposed CFD methodology was then successfully applied to model a detonation event that occurred during liquid oxygen/gaseous hydrogen rocket diffuser testing at NASA Stennis Space Center.
Document ID
20160006890
Acquisition Source
Stennis Space Center
Document Type
Technical Publication (TP)
Authors
Allgood, Daniel C.
(NASA Stennis Space Center Stennis Space Center, MS, United States)
Date Acquired
June 1, 2016
Publication Date
April 1, 2016
Subject Category
Propellants And Fuels
Fluid Mechanics And Thermodynamics
Report/Patent Number
NASA/TP-2016-219220
SSTI-8076-0003
Report Number: NASA/TP-2016-219220
Report Number: SSTI-8076-0003
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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