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Aeropropulsive characteristics of isolated combined turbojet/ramjet nozzles at Mach numbers from 0 to 1.20An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine the aeropropulsive performance characteristics (the aerodynamic quantities affected by propulsion) of 13 isolated combined turbojet/ramjet nozzle configurations. These configurations simulated the variable-geometry features of two nozzle designs designated as the multiple-expansion ramp nozzle (MERN) and the composite contour nozzle (CCN). Test data were obtained at static conditions and at Mach numbers of 0.60, 0.90, and 1.20 with jet exhaust simulated by high-pressure air. The results showed that the CCN had the higher performance over the Mach number range than the MERN, as indicated by the difference of thrust minus drag divided by ideal thrust. Increasing the ramjet throat area for the MERN resulted in an increase in performance that increased with Mach number. For the CCN at Mach numbers less than 1.20, increasing the ramjet throat area resulted in a loss in performance.
Document ID
19880014373
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Carson, George T., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Lamb, Milton
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
June 1, 1988
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:2814
L-16390
NASA-TP-2814
Accession Number
88N23757
Funding Number(s)
PROJECT: RTOP 505-62-91-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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