Altitude wind tunnel investigation of the prototype J40-WE-8 turbojet engine without afterburner

McAulay, John E., Kaufman, Harold R.
naca-rm-e52k10
1953


An investigation was conducted in the Lewis altitude wind tunnel to evaluate the performance characteristics of the prototype J40-WE-8 turbojet engine without afterburner. Data were obtained with an electronic control operative and inoperative. The performance data were obtained at altitudes from 15,000 to 60,000 feet and flight Mach numbers of 0.17 to 1.68. At corrected engine speeds of 7000 rpm and above, an increase in altitude resulted in an increase in correct net thrust and had no effect on corrected air flow. A method is presented to define the effect of changes in engine operating and flight conditions on the pumping and air-flow characteristics and the combustion efficiency.

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