Altitude-wind-tunnel investigation of a 3000-pound-thrust axial-flow turbojet engine:III. Analysis of combustion-chamber performance

Campbell, Carl E.
naca-rm-e8b19
1948


Combustion-chamber performance characteristics of a 3000-pound-thrust axial-flow turbojet engine have been determined from an investigation of the complete engine in the Cleveland altitude wind tunnel over a range of simulated altitudes and flight Mach numbers. The effect of variations in altitude and flight Mach number on combustion efficiency, combustion-chamber total-pressure losses, engine-cycle efficiency, and the fractional loss in engine-cycle efficiency resulting from combustion-chamber pressure losses is presented for various engine configurations.

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