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An approximate theoretical method for modeling the static thrust performance of non-axisymmetric two-dimensional convergent-divergent nozzlesAn analytical/numerical method has been developed to predict the static thrust performance of non-axisymmetric, two-dimensional convergent-divergent exhaust nozzles. Thermodynamic nozzle performance effects due to over- and underexpansion are modeled using one-dimensional compressible flow theory. Boundary layer development and skin friction losses are calculated using an approximate integral momentum method based on the classic karman-Polhausen solution. Angularity effects are included with these two models in a computational Nozzle Performance Analysis Code, NPAC. In four different case studies, results from NPAC are compared to experimental data obtained from subscale nozzle testing to demonstrate the capabilities and limitations of the NPAC method. In several cases, the NPAC prediction matched experimental gross thrust efficiency data to within 0.1 percent at a design NPR, and to within 0.5 percent at off-design conditions.
Document ID
19950016776
Acquisition Source
Legacy CDMS
Document Type
Thesis/Dissertation
Authors
Hunter, Craig A. (Joint Inst. for Advancement of Flight Sciences Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1995
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:195050
NASA-CR-195050
Accession Number
95N23193
Funding Number(s)
CONTRACT_GRANT: NCC1-24
PROJECT: RTOP 537-07-20
CONTRACT_GRANT: NCC1-14
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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