Actions for RAXJET : A computer program for predicting transonic, axisymmetric flow over nozzle afterbodies with supersonic jet exhausts

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RAXJET : A computer program for predicting transonic, axisymmetric flow over nozzle afterbodies with supersonic jet exhausts

Author
Wilmoth, R. G.
Published
Feb 1, 1982.
Physical Description
1 electronic document
Online Version

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Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
A viscous-inviscid interaction method to calculate the subsonic and transonic flow over nozzle afterbodies with supersonic jet exhausts was developed. The method iteratively combines a relaxation solution of the full potential equation for the inviscid external flow, a shock capturing-shock fitting inviscid jet solution, an integral boundary layer solution, a control volume method for treating separated flows, and an overlaid mixing layer solution. A computer program called RAXJET which incorporates the method, illustrates the predictive capabilities of the method by comparison with experimental data is described, a user's guide to the computer program is provided. The method accurately predicts afterbody pressures, drag, and flow field properties for attached and separated flows for which no shock induced separation occurs.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19820011301.
Accession ID: 82N19175.
L-14789.
NASA-TM-83235.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15716873