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Euler solutions for an unbladed jet engine configurationA Euler solution for an axisymmetric jet engine configuration without blade effects is presented. The Euler equations are solved on a multiblock grid which covers a domain including the inlet, bypass duct, core passage, nozzle, and the far field surrounding the engine. The simulation is verified by considering five theoretical properties of the solution. The solution demonstrates both multiblock grid generation techniques and a foundation for a full jet engine throughflow calculation.
Document ID
19920002110
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Stewart, Mark E. M. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1991
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-TM-105332
NAS 1.15:105332
E-6695
ICOMP-91-23
Report Number: NASA-TM-105332
Report Number: NAS 1.15:105332
Report Number: E-6695
Report Number: ICOMP-91-23
Meeting Information
Meeting: Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 6, 1991
End Date: January 9, 1991
Sponsors: AIAA
Accession Number
92N11328
Funding Number(s)
PROJECT: RTOP 505-62-21
CONTRACT_GRANT: NASA ORDER C-99066-G
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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