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Investigation of Low-Reynolds-Number Rocket Nozzle Design Using PNS-Based Optimization ProcedureAn optimization approach to rocket nozzle design, based on computational fluid dynamics (CFD) methodology, is investigated for low-Reynolds-number cases. This study is undertaken to determine the benefits of this approach over those of classical design processes such as Rao's method. A CFD-based optimization procedure, using the parabolized Navier-Stokes (PNS) equations, is used to design conical and contoured axisymmetric nozzles. The advantage of this procedure is that it accounts for viscosity during the design process; other processes make an approximated boundary-layer correction after an inviscid design is created. Results showed significant improvement in the nozzle thrust coefficient over that of the baseline case; however, the unusual nozzle design necessitates further investigation of the accuracy of the PNS equations for modeling expanding flows with thick laminar boundary layers.
Document ID
19970004933
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Hussaini, M. Moin (NASA Langley Research Center Hampton, VA United States)
Korte, John J. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
November 1, 1996
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:110295
NASA-TM-110295
Report Number: NAS 1.15:110295
Report Number: NASA-TM-110295
Accession Number
97N12934
Funding Number(s)
PROJECT: RTOP 522-31-31-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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