Preliminary Transient Performance Data on the J73 Turbojet Engine, 3: Altitude, 45,000 Feet Page: 52 of 96
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NACA RM SE53F30
CONFIDENTIAL
5Pen limit
- -234Dynamic pressure at engine inletp lb/aq ft abs
Calibration 1.240 (1b/sq ft)/mm
Time 1 sec-N
Engine-inlet total pressure in. Hg abs
Calibration .062 in. g/mm
:u - A - 4 -
62 - _-A --t'-,::
8.82A1 0/.1 1 ! ! - // _L : :L ,-
Compressor-outlet total pressure, in. I5 abs
Calibration 0.658 in. Eg/mmI-
720 - --
Exhaust-gas temperature OF (uncompensated)
Calibration 31.1 OF/mm
I IIII=IILI
Engine speed, rpm
- Calibration 63 rpm/MM r-._
" . f - , l I I t I ------Figure 32
Oscillograph traces showing variations of different engine parameters during
in fuel flow. Altitude, 45,000 feet; flight Macb number, 0.8; engine-inlet
ture, 300 F; inlet guide vanes position, open.a step-change
air tempera-CONFIDENTIAL
51
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McAulay, John E. & Wallner, Lewis E. Preliminary Transient Performance Data on the J73 Turbojet Engine, 3: Altitude, 45,000 Feet, report, July 16, 1953; (https://digital.library.unt.edu/ark:/67531/metadc65444/m1/52/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.