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NLS nozzle base flow characteristicsThe flow characteristics of the National Launch System (NLS) nozzle base area need to be determined in order for heat transfer rates to be estimated. The objective of this work is to calculate these flow characteristics using computational fluid dynamics (CFD). A full Navier-Stokes code in an axisymmetric mode, using a kappa-epsilon model with wall functions is applied. Calculations were completed at an altitude of 3,250 and 80,000 feet in the flight trajectory. The results show flow features which can affect vehicle design. Calibration of a 3-D case with data is underway. Information is given in viewgraph form.
Document ID
19920023008
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Erhart, John J. (Pratt and Whitney Aircraft West Palm Beach, FL, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1992
Publication Information
Publication: NASA. Goddard Space Flight Center, Tenth Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion, Part 2
Subject Category
Fluid Mechanics And Heat Transfer
Accession Number
92N32252
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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