A parametric propulsion system analysis has been conducted to assess the subsonic endurance potential, cycle characteristics, and technology payoff for turbofan engines specifically matched for high altitude operation. From the analysis, the following conclusions have been drawn: (1) when properly matched, the turbofan engine is superior in endurance performace to the turbojet at high altitudes; (2) due to Reynolds number effects one large, all-axial engine is superior to two smaller equivalent designs; (3) projected advanced engine technology has produced reductions in engine plus fuel weight on the order of 14 to 16% over present-day designs; (4) the requirement for higher endurance altitudes can result in a significant reduction in endurance time for a given level of aircraft and engine technology. (Author)


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