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Flight evaluation of a simplified gross thrust calculation technique using an F100 turbofan engine in an F-15 airplaneA simplified gross thrust calculation technique was evaluated in flight tests on an F-15 aircraft using prototype F100-PW-100 engines. The technique relies on afterburner duct pressure measurements and empirical corrections to an ideal one-dimensional analysis to determine thrust. In-flight gross thrust calculated by the simplified method is compared to gross thrust calculated by the engine manufacturer's gas generator model. The evaluation was conducted at Mach numbers from 0.6 to 1.5 and at altitudes from 6000 meters to 13,700 meters. The flight evaluation shows that the simplified gross thrust method and the gas generator method agreed within plus or minus 3 percent. The discrepancies between the data generally fell within an uncertainty band derived from instrumentation errors and recording system resolution.
Document ID
19810006485
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Kurtenbach, F. J. (NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Burcham, F. W., Jr. (NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1981
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
H-1118
NASA-TP-1782
Report Number: H-1118
Report Number: NASA-TP-1782
Accession Number
81N15000
Funding Number(s)
PROJECT: RTOP 506-51-34
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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