Accession Number : AD0531789

Title :   Subsonic, High Altitude Propulsion System Analysis

Descriptive Note : Final rept. Jun 72-Sep 73,

Corporate Author : AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Ruble,Jim ; Dienstberger,Carl , Jr

Report Date : JUL 1974

Pagination or Media Count : 94

Abstract : 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)

Descriptors :   (*Turbofan engines, Remotely piloted vehicles), (*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)

Subject Categories : Patrol and Reconnaissance Aircraft
      Pilotless Aircraft
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE