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altitude operational characteristics of prototype j40-we-8 turbojet engineThe altitude operational characteristics of the prototype J40-WE-8 turbojet engine were determined in the NACA Lewis altitude wind tunnel. The operational characteristics that were obtained include (1) compressor surge characteristics, (2) acceleration and deceleration rates, (3) steady-state windmilling-engine characteristics, (4) altitude ignition characteristics, and (5) the effect of two grades of fuel on steady-state engine performance at an altitude of 45,000 feet and a flight Mach number of 0.20. The altitude ignition characteristics determined include the effects of (1) ignition fuel flow, (2) two ignition procedures, (3) fuel temperatures, and (4) two grades of fuel on ignition characteristics. The compressor surge line, when presented as a function of compressor pressure ratio and corrected engine speed, was not affected by changes in flight condition and was independent of engine-inlet installation and of the manner in which surge was approached, rapidly or slowly. Also there was no effect of altitude or engine-inlet installation on the compressor surge recovery line when presented as a function of compressor pressure ratio and corrected engine speed.
Document ID
19930087629
Document Type
Other
Authors
Sobolewski, Adam E
Lubick, Robert J
Date Acquired
August 16, 2013
Publication Date
August 14, 1953
Report/Patent Number
NACA-RM-E52L29
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
FUELS - RELATION TO ENGINE PERFORMANCE
COMBUSTION - EFFECT OF ENGINE OPERATING CONDITIONS AND COMBUSTION-CHAMBER GEOMET
ENGINES, CONTROL - TURBOJET
ENGINES, TURBOJET
COMPRESSORS - AXIAL-FLOW

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