Altitude Performance Characteristics of the J73-GE-1A Turbojet Engine Page: 2 of 36
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NACA RM E53125 UNCLASIIFEI
3 1176 01435 2927 UNCLASIFIED
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
RESEARCH MEMORANDUM
ALTITUDE PERFORMANCE CHARACTERISTICS OF THE
J73-GE-1A TURBOJET ENGINE
By Carl E. Campbell and E. William Conrad
SUMMARY
An investigation was conducted in an altitude test chamber at the
NACA Lewis laboratory to determine the performance characteristics of
the J73-GE-1A turbojet engine. This model engine had a fixed-area ex-
haust nozzle and was the first of a series of J73 production engines.
Performance data were obtained at simulated altitudes from 15,000 to
55,000 feet and at flight Mach numbers from approximately 0.07 to 1.01,
which correspond to a range of compressor-inlet Reynolds number index
values from 0.90 to 0.13.
Engine performance is presented in the form of engine pumping char-
acteristics and combustion efficiency, from which the over-all perform-
ance may be calculated for any flight condition within the range of
Reynolds number indices covered by the experimental data. Curves of
net thrust and fuel flow, computed from these data, are presented as
functions of true airspeed for four altitudes. Data are also included
to enable the determination of thrust in flight.
INTRODUCTION
An investigation was conducted in an altitude test chamber at the
NACA Lewis laboratory to determine the complete performance and opera-
tional characteristics of the J73 turbojet engine. The first phase of
this program, which is reported herein, was an altitude-performance
evaluation of the J73-GE-1A engine. Pending development of an improved
control, this engine had a turbine-nozzle area ten percent larger than
the design area for later engine models in order to avoid compressor
surge during flight tests. The engine also incorporated variable
compressor-inlet guide vanes to avoid part-speed surge. Throughout the
investigation reported herein, however, the guide vanes were fixed at
the design angle for the high engine speed range (130 from axial).
UNCLASSIFIED
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Campbell, Carl E. & Conrad, E. William. Altitude Performance Characteristics of the J73-GE-1A Turbojet Engine, report, December 9, 1954; (https://digital.library.unt.edu/ark:/67531/metadc59886/m1/2/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.