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Afterbody External Aerodynamic and Performance Prediction at High Reynolds NumbersThis CFD experiment concludes that the potential difference between the flow between a flight Reynolds number test and a sub-scale wind tunnel test are substantial for this particular nozzle boattail geometry. The early study was performed using a linear k-epsilon turbulence model. The present study was performed using the Girimaji formulation of a algebraic Reynolds stress turbulent simulation.
Document ID
20000044630
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Carlson, John R. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
August 19, 2013
Publication Date
December 1, 1999
Publication Information
Publication: First NASA/Industry High-Speed Research Configuration Aerodynamics Workshop
Issue: Part 1
Subject Category
Aerodynamics
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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