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Numerical method for predicting flow characteristics and performance of nonaxisymmetric nozzles. Part 2: ApplicationsA computer implemented numerical method for predicting the flow in and about an isolated three dimensional jet exhaust nozzle is summarized. The approach is based on an implicit numerical method to solve the unsteady Navier-Stokes equations in a boundary conforming curvilinear coordinate system. Recent improvements to the original numerical algorithm are summarized. Equations are given for evaluating nozzle thrust and discharge coefficient in terms of computed flowfield data. The final formulation of models that are used to simulate flow turbulence effect is presented. Results are presented from numerical experiments to explore the effect of various quantities on the rate of convergence to steady state and on the final flowfield solution. Detailed flowfield predictions for several two and three dimensional nozzle configurations are presented and compared with wind tunnel experimental data.
Document ID
19800024846
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Thomas, P. D. (Lockheed Missiles and Space Co. Palo Alto, CA, United States)
Date Acquired
September 4, 2013
Publication Date
October 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
LMSC-D678888-PT-2
NASA-CR-3264
Accession Number
80N33354
Funding Number(s)
CONTRACT_GRANT: NAS1-15084
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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