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Analysis and design of three dimensional supersonic nozzles. Volume 1 : Nozzle-exhaust flow field analysis by a reference plane characteristics technique

Author
Dash, S.
Published
Oct 1, 1972.
Physical Description
1 electronic document
Additional Creators
Delguidice, P.
Online Version

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Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
A second order numerical method employing reference plane characteristics has been developed for the calculation of geometrically complex three dimensional nozzle-exhaust flow fields, heretofore uncalculable by existing methods. The nozzles may have irregular cross sections with swept throats and may be stacked in modules using the vehicle undersurface for additional expansion. The nozzles may have highly nonuniform entrance conditions, the medium considered being an equilibrium hydrogen-air mixture. The program calculates and carries along the underexpansion shock and contact as discrete discontinuity surfaces, for a nonuniform vehicle external flow.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19740003000.
Accession ID: 74N11113.
ATL-TR-166-VOL-1.
NASA-CR-132350.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15746881