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)
Subsonic, High Altitude Propulsion System Analysis
1974
94 pages
Report
No indication
English
Jet & Gas Turbine Engines , Aircraft , Turbofan engines , Turbojet engines , Remotely piloted vehicles , Propulsion systems , Jet propulsion , Subsonic flight , Subsonic characteristics , Reconnaissance aircraft , Surveillance drones , High altitude , Mach number , Reynolds number , Mission profiles , Variables , Jet engine fuels , Jet engine inlets , Sea level , Cooling , Weight , Pressure , Temperature , Thrust , Altitude , Endurance(General) , Performance(Engineering)
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