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User's guide for NASCRIN: A vectorized code for calculating two-dimensional supersonic internal flow fieldsA computer program NASCRIN has been developed for analyzing two-dimensional flow fields in high-speed inlets. It solves the two-dimensional Euler or Navier-Stokes equations in conservation form by an explicit, two-step finite-difference method. An explicit-implicit method can also be used at the user's discretion for viscous flow calculations. For turbulent flow, an algebraic, two-layer eddy-viscosity model is used. The code is operational on the CDC CYBER 203 computer system and is highly vectorized to take full advantage of the vector-processing capability of the system. It is highly user oriented and is structured in such a way that for most supersonic flow problems, the user has to make only a few changes. Although the code is primarily written for supersonic internal flow, it can be used with suitable changes in the boundary conditions for a variety of other problems.
Document ID
19860014094
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Kumar, A. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
February 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
L-15678
NAS 1.15:85708
NASA-TM-85708
Accession Number
86N23565
Funding Number(s)
PROJECT: RTOP 505-43-83-06
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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