NDLI: Thrust chamber performance using navier-stokes solution. [space shuttle main engine viscous nozzle calculation]

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Thrust chamber performance using navier-stokes solution. [space shuttle main engine viscous nozzle calculation]

Content Provider	NASA Technical Reports Server (NTRS)
Author	Chan, J. S. Freeman, J. A.
Copyright Year	1984
Description	The viscous, axisymmetric flow in the thrust chamber of the space shuttle main engine (SSME) was computed on the CRAY 205 computer using the general interpolants method (GIM) code. Results show that the Navier-Stokes codes can be used for these flows to study trends and viscous effects as well as determine flow patterns; but further research and development is needed before they can be used as production tools for nozzle performance calculations. The GIM formulation, numerical scheme, and computer code are described. The actual SSME nozzle computation showing grid points, flow contours, and flow parameter plots is discussed. The computer system and run times/costs are detailed.
File Size	5206862
Page Count	90
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19850010709
Archival Resource Key	ark:/13960/t9f52hd0c
Language	English
Publisher Date	1984-12-12
Access Restriction	Open
Subject Keyword	Spacecraft Propulsion And Power Computational Fluid Dynamics Axisymmetric Flow Finite Element Method Navier-stokes Equation Nozzle Geometry Interpolation Three Dimensional Flow Nozzle Flow Finite Difference Theory Differential Equations Space Shuttle Main Engine Thrust Chambers Cobalt Acetates Weighting Functions Viscous Flow 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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