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Computer program for calculating the flow field of supersonic ejector nozzlesAn analytical procedure for computing the performance of supersonic ejector nozzles is presented. This procedure includes real sonic line effects and an interaction analysis for the mixing process between the two streams. The procedure is programmed in FORTRAN 4 and has operated successfully on IBM 7094, IBM 360, CDC 6600, and Univac 1108.
Document ID
19740012321
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Anderson, B. H. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1974
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TN-D-7602
E-7476
Accession Number
74N20434
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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