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Preliminary Transient Performance Data on the J73 Turbojet Engine. II - Altitude, 35,000 FeetA program was undertaken to determine the J73 turbojet engine compressor stall and surge characteristics and combustor blow-out limits encountered during transient engine operation. Data were obtained in the form of oscillograph traces showing the time history of several engine performance parameters with changes in engine fuel flow. The data presented in this report are for step changes in fuel flow at an altitude of 35,000 feet, at flight Mach numbers of 0.3, 0.8, and 1.2, and at several engine-inlet temperatures,
Document ID
20090026528
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Lubick, Robert J. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Sobolewski, Adam E. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
June 29, 1953
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-RM-SE53F29
Report Number: NACA-RM-SE53F29
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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