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Preliminary Altitude Performance Data for the J71-A2 (X-26) Turbojet EngineData were obtained in an altitude test chamber for a range of altitudes from 20,000 to 58,000 feet at a flight Mach number of 0.9, and for several flight Mach numbers at an altitude of 45,000 feet. Data approximating sea-level operation are also included. Engine component performance data are presented in addition to windmilling, exhaust-nozzle, and ejector performance.
Document ID
20090021953
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Useller, James W. (NASA Lewis Research Center Cleveland, OH, United States)
Mallett, William E. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
August 19, 1954
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-RM-SE54H06
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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