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Injector Design Tool Improvements: User's manual for FDNS V.4.5The major emphasis of the current effort is in the development and validation of an efficient parallel machine computational model, based on the FDNS code, to analyze the fluid dynamics of a wide variety of liquid jet configurations for general liquid rocket engine injection system applications. This model includes physical models for droplet atomization, breakup/coalescence, evaporation, turbulence mixing and gas-phase combustion. Benchmark validation cases for liquid rocket engine chamber combustion conditions will be performed for model validation purpose. Test cases may include shear coaxial, swirl coaxial and impinging injection systems with combinations LOXIH2 or LOXISP-1 propellant injector elements used in rocket engine designs. As a final goal of this project, a well tested parallel CFD performance methodology together with a user's operation description in a final technical report will be reported at the end of the proposed research effort.
Document ID
19990045901
Acquisition Source
Marshall Space Flight Center
Document Type
Other
Authors
Chen, Yen-Sen
(Engineering Sciences, Inc. Huntsville, AL United States)
Shang, Huan-Min
(Engineering Sciences, Inc. Huntsville, AL United States)
Wei, Hong
(Engineering Sciences, Inc. Huntsville, AL United States)
Liu, Jiwen
(Engineering Sciences, Inc. Huntsville, AL United States)
Date Acquired
September 6, 2013
Publication Date
April 4, 1998
Subject Category
Engineering (General)
Funding Number(s)
CONTRACT_GRANT: NASA Order H-28612-D
Distribution Limits
Public
Copyright
Public Use Permitted.
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