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Supersonic STOVL ejector aircraft from a propulsion point of viewA baseline supersonic STOVL ejector aircraft, its propulsion and typical operating modes is described, and important propulsion parameters are identified. Then a number of propulsion system changes are evaluated for improvement of the lift-off performance aft deflection of the ejector jet and heating of the ejector primary air either by burning or using the hot engine core flow. The possibility for cooling the footprint is illustrated for mixing or interchanging the fan and core flows, and in use of a core flow ejector. The application of a new engine concept the turbine bypass engine plus a turbocompressor to supply the ejector primary air, and thrust during takeoff combat are presented.
Document ID
19840016513
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Luidens, R. W. (NASA Lewis Research Center Cleveland, OH, United States)
Plencner, R. (NASA Lewis Research Center Cleveland, OH, United States)
Haller, W. (NASA Lewis Research Center Cleveland, OH, United States)
Glassman, A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1984
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TM-83641
E-2084
NAS 1.15:83641
Meeting Information
Meeting: Joint Propulsion Conf.
Location: Cincinnati, OH
Country: United States
Start Date: June 11, 1984
End Date: June 13, 1984
Sponsors: AIAA, SAE, ASME
Accession Number
84N24581
Funding Number(s)
PROJECT: RTOP 505-40-82
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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