Advanced Propulsion Technology Assessment for an Externally Blown Flap Transport
Abstract
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 thrust/weight 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 thrust/weight 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 thrust/weight 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 thrust/weight turbofan propulsion systems for the 1980+ time period.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1972
- Accession Number
- AD0905701
Entities
People
- Carl F. Dienstberger Jr.
- James R. Ruble
- Raymond N. Leo
- Richard J. Krabal
Organizations
- Air Force Research Laboratory