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Transonic, Axisymmetric Flow Over Nozzle Afterbodies With Supersonic Jet ExhaustsPredictions require less computation than Navier-Stokes solutions. RAXJET computer program predicts transonic, axisymmetric flow over nozzle afterbodies with supersonic jet exhausts and includes effects of boundarylayer displacement, separation, jet entrainment, and inviscid jet plume blockage. RAXJET written in FORTRAN IV.
Document ID
19830000187
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Wilmoth, R. G.
Date Acquired
August 11, 2013
Publication Date
October 1, 1983
Publication Information
Publication: NASA Tech Briefs
Volume: 7
Issue: 4
ISSN: 0145-319X
Subject Category
Mechanics
Report/Patent Number
LAR-12957
Accession Number
83B10187
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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