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Comparison of performance of AN-F-58 and AN-F-32 fuels in J33-A-23 turbojet engine
Report presenting an investigation using a 4600 pound-thrust turbojet engine as part of a program to determine the comparative performance of fuels conforming to specifications AN-F-58 and AN-F-32. Results regarding the altitude performance, altitude low-speed blow-out limits, idling limits of fuel-metering control, altitude windmilling starts, carbon-deposition rates, and iron oxide contamination are provided.
Date:
June 2, 1949
Creator:
Wilsted, H. D. & Armstrong, J. C.
System:
The UNT Digital Library
Flight Investigation of the Jettisonable-Nose Method of Pilot Escape Using Rocket-Propelled Models
Report discussing testing using two rocket-propelled models to test the jettisonable-nose method of pilot escape. The nose was jettisoned successfully on the second attempt and the accelerations produced were found to be within human tolerance. The first test ended with a collision of the nose and wing, indicating that this is a possible risk during power-on flight.
Date:
June 2, 1949
Creator:
Lundstrom, Reginald R. & O'Kelly, Burke R.
System:
The UNT Digital Library
Altitude-Test-Chamber Investigation of McDonnell Afterburner on J34 Engine
"An altitude-test-chamber investigation was conducted to determine the operational and performance characteristics of a McDonnell afterburner with a fixed-area exhaust nozzle on a J34 engine. At rated engine speed, the altitude limit, as determined by combustion blow-out, occurred as a band of unstable operation of about 6000-foot altitude in width with minimum altitude limits from 31,000 feet at a simulated flight Mach number of 0.40 to about 45,500 feet at a simulated flight Mach number of 1.00. Considerable difficulty was experienced in attempting to establish or maintain balanced-cycle engine operation at altitudes above 36,000 feet" (p. 1).
Date:
June 2, 1949
Creator:
Reller, John O. & Dowman, Harry W.
System:
The UNT Digital Library