Advanced Propulsion Technology Assessment for an Externally Blown Flap Transport
Final rept. May 1970-Jan 1971
AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OH
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Results of the study indicate that, for an externally blown flap transport aircraft and missions investigated, aircraft gross weight reductions of 9 to 12.5 can be obtained from the utilization of turbofan engines incorporating Advanced Technology Components. Engine thrustweight ratio was clearly the most significant propulsion design parameter in terms of providing aircraft weight reductions. Other propulsion parameters such as cruise SFC, bypass ratio, and overall pressure ratio had only secondary effects on aircraft gross weight. While the effect of noise abatement was not considered, variations of engine thrustweight ratio and cruise SFC were evaluated. Using these variations, preliminary estimates of the penalties associated with noise can be obtained by expressing it in terms of an engine thrustweight reduction and cruise SFC increase and assessing the resultant aircraft weight increase. A recommendation is made to initiate a preliminary design activity whose objective would be to define suitable, high thrustweight turbofan propulsion systems for the 1980 time period.
- Transport Aircraft
- Jet and Gas Turbine Engines