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An engine trade study for a supersonic STOVL fighter-attack aircraft, volume 1The best main engine for an advanced STOVL aircraft flight demonstrator was studied. The STOVL aircraft uses ejectors powered by engine bypass flow together with vectored core exhaust to achieve vertical thrust capability. Bypass flow and core flow are exhausted through separate nozzles during wingborne flight. Six near term turbofan engines were examined for suitability for this aircraft concept. Fan pressure ratio, thrust split between bypass and core flow, and total thrust level were used to compare engines. One of the six candidate engines was selected for the flight demonstrator configuration. Propulsion related to this aircraft concept was studied. A preliminary candidate for the aircraft reaction control system for hover attitude control was selected. A mathematical model of transfer of bypass thrust from ejectors to aft directed nozzle during the transition to wingborne flight was developed. An equation to predict ejector secondary air flow rate and ram drag is derived. Additional topics discussed include: nozzle area control, ejector to engine inlet reingestion, bypass/core thrust split variation, and gyroscopic behavior during hover.
Document ID
19850002602
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Beard, B. B. (General Dynamics Corp. Fort Worth, TX, United States)
Foley, W. H. (General Dynamics Corp. Fort Worth, TX, United States)
Date Acquired
September 5, 2013
Publication Date
February 1, 1982
Subject Category
Aeronautics (General)
Report/Patent Number
NASA-CR-166304
NAS 1.26:166304
Accession Number
85N10910
Funding Number(s)
CONTRACT_GRANT: NAS2-10981
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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