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Validation of the SINDA/FLUINT Code Using Several Analytical SolutionsThe Systems Improved Numerical Differencing Analyzer and Fluid Integrator (SINDA/FLUINT) code has often been used to determine the transient and steady-state response of various thermal and fluid flow networks. While this code is an often used design and analysis tool, the validation of this program has been limited to a few simple studies. For the current study, the SINDA/FLUINT code was compared to four different analytical solutions. The thermal analyzer portion of the code (conduction and radiative heat transfer, SINDA portion) was first compared to two separate solutions. The first comparison examined a semi-infinite slab with a periodic surface temperature boundary condition. Next, a small, uniform temperature object (lumped capacitance) was allowed to radiate to a fixed temperature sink. The fluid portion of the code (FLUINT) was also compared to two different analytical solutions. The first study examined a tank filling process by an ideal gas in which there is both control volume work and heat transfer. The final comparison considered the flow in a pipe joining two infinite reservoirs of pressure. The results of all these studies showed that for the situations examined here, the SINDA/FLUINT code was able to match the results of the analytical solutions.
Document ID
19950020929
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
John R Keller
(Lockheed Engineering & Sciences Company Hampton, Virginia., United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1995
Publication Information
Publication: The Sixth Annual Thermal and Fluids Analysis Workshop
Publisher: National Aeronautics and Space Administration
Subject Category
Fluid Mechanics and Thermodynamics
Report/Patent Number
CP-10161
Meeting Information
Meeting: The Sixth Annual Thermal and Fluids Analysis Workshop
Location: Brook Park, OH
Country: US
Start Date: August 15, 1994
End Date: August 19, 1994
Sponsors: National Aeronautics and Space Administration, Ohio Aerospace Institute
Accession Number
95N27350
Distribution Limits
Public
Copyright
Portions of document may include copyright protected material.
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