NDLI: Development of tripropellant cfd design code

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Development of tripropellant cfd design code

Content Provider	NASA Technical Reports Server (NTRS)
Author	Farmer, Richard C. Cheng, Gary C. Anderson, Peter G.
Copyright Year	1998
Description	A tripropellant, such as GO2/H2/RP-1, CFD design code has been developed to predict the local mixing of multiple propellant streams as they are injected into a rocket motor. The code utilizes real fluid properties to account for the mixing and finite-rate combustion processes which occur near an injector faceplate, thus the analysis serves as a multi-phase homogeneous spray combustion model. Proper accounting of the combustion allows accurate gas-side temperature predictions which are essential for accurate wall heating analyses. The complex secondary flows which are predicted to occur near a faceplate cannot be quantitatively predicted by less accurate methodology. Test cases have been simulated to describe an axisymmetric tripropellant coaxial injector and a 3-dimensional RP-1/LO2 impinger injector system. The analysis has been shown to realistically describe such injector combustion flowfields. The code is also valuable to design meaningful future experiments by determining the critical location and type of measurements needed.
File Size	2457629
Page Count	60
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19980048420
Archival Resource Key	ark:/13960/t27993r80
Language	English
Publisher Date	1998-05-01
Access Restriction	Open
Subject Keyword	Propellants And Fuels Combustion Physics Position Location Injectors Computational Fluid Dynamics Heating Liquid Rocket Propellants Flow Distribution Rocket Engines Combustion Sprayers Gas Temperature Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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