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Experimental evaluation of expendable supersonic nozzle conceptsExhaust nozzles for expendable supersonic turbojet engine missile propulsion systems are required to be simple, short and compact, in addition to having good broad-range thrust-minus-drag performance. A series of convergent-divergent nozzle scale model configurations were designed and wind tunnel tested for a wide range of free stream Mach numbers and nozzle pressure ratios. The models included fixed geometry and simple variable exit area concepts. The experimental and analytical results show that the fixed geometry configurations tested have inferior off-design thrust-minus-drag performance in the transonic Mach range. A simple variable exit area configuration called the Axi-Quad nozzle, combining features of both axisymmetric and two-dimensional convergent-divergent nozzles, performed well over a broad range of operating conditions. Analytical predictions of the flow pattern as well as overall performance of the nozzles, using a fully viscous, compressible CFD code, compared very well with the test data.
Document ID
19900055636
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Baker, V.
(General Motors Corp. Indianapolis, IN, United States)
Kwon, O.
(General Motors Corp. Indianapolis, IN, United States)
Vittal, B.
(General Motors Corp. Allison Gas Turbine Div., Indianapolis, IN, United States)
Berrier, B.
(General Motors Corp. Indianapolis, IN, United States)
Re, R.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1990
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 90-1904
Accession Number
90A42691
Distribution Limits
Public
Copyright
Other

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