Measurement Effects on the Calculation of In-Flight Thrust for an F404 Turbofan Engine

Conners, Timothy R. (1989) Measurement Effects on the Calculation of In-Flight Thrust for an F404 Turbofan Engine. Technical Report NASA TM-4140, Research Engineering, NASA Dryden Flight Research Center.

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Abstract

A study has been performed that investigates parameter measurement effects on calculated in-flight thrust for the General Electric F404-GE-400 afterburning turbofan engine which powered the X-29A forward-swept wing research aircraft. Net-thrust uncertainty and influence coefficients were calculated and are presented. Six flight conditions were analyzed at five engine power settings each. Results were obtained using the mass flow-temperature and area-pressure thrust calculation methods, both based on the commonly used gas generator technique. Thrust uncertainty was determined using a common procedure based on the use of measurement uncertainty and influence coefficients. The effects of data nonlinearity on the uncertainty calculation procedure were studied and results are presented. The advantages and disadvantages of using this particular uncertainty procedure are discussed. A brief description of the thrust-calculation technique along with the uncertainty calculation procedure is included.

EPrint Type:	NASA Technical Memorandum
Keywords:	F404 turbofan engine, Influence coefficient, Measurement uncertainty, Performance, Thrust Calculation, Thrust uncertainty
Subjects:	(01 - 09) Aeronautics: (07) Aircraft Propulsion And Power Aircraft/Project: X-29
ID Code:	400
Deposited On:	16 Febuary 2005
Additional Information:	24 pages. Prepared as AIAA Paper 89-2364 for presentation at the AIAA Joint Propulsion Conference, Monterey, California, July 10–14, 1989.