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Effects of inlet distortion on a static pressure probe mounted on the engine hub in an F-15 airplaneProblems encountered in obtaining good engine face pressure data were studied. A single static measurement located upstream of the engine hub in the stream flow was found to provide a pressure signal suitable for engine control. Two identical probes for measuring fan inlet static (PS2) pressure were designed and mounted on the hub of the left F100-PW-100 turbofan engine installed in the F-15 test aircraft for flight evaluation. The probe is used as a static pressure sensor for a digital engine control system.
Document ID
19860015876
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hughes, D. L. (NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Mackall, K. G. (NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Date Acquired
August 12, 2013
Publication Date
March 1, 1984
Publication Information
Publication: Digital Electronic Engine Control Flight Evaluation in an F-15 Airplane
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
PAPER-5
Report Number: PAPER-5
Accession Number
86N25347
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

IDRelationTitle19860015871Collected WorksDigital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane19860015871Collected WorksDigital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane
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