Accession Number : ADP006252
Title : Improving Military Transport Aircraft through Highly Integrated Engine-Wing Design,
Corporate Author : SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION PARIS (FRAN CE)
Personal Author(s) : Lardellier, A.
Report Date : DEC 1990
Pagination or Media Count : 15
Abstract : Current studies have shown the interest of very large bypass ratio engines (10 < BPR < 14) to power Long Range Airliners, at cruise speed exceeding Mach 0.8. A further benefit in term of installed SFC can be expected for the Future Large Aircraft (FLA), cruising at Mach 0.75. Compared to an equivalent turbofan, a very large bypass engine can deliver a higher thrust during take off, thus improving the high lift capability of the aircraft. Taking into account that a conventional front fan engine is likely to show a large Radar Cross Section (RCS), and that this problem would have to be addressed for FLA, the engine preferred concept is a Ducted Aft Contrafan. The resulting high hub-tip ratio fan flow path, combined with slow rotating composite fan-blades is indeed a good approach toward reduction of the engine RCS. In order to minimize the extra-weight due to the long duct, a highly integrated engine-wing design is proposed, offering a reduced friction drag; particular attention is paid to the maintenance and transportation problems.
Descriptors : AIRCRAFT, DRAG REDUCTION, DUCTS, ENGINES, FRICTION, HIGH LIFT, MILITARY AIRCRAFT, RADAR CROSS SECTIONS, REDUCTION, THRUST, TRANSPORT AIRCRAFT, TRANSPORTATION, TURBOFAN ENGINES, VELOCITY.
Subject Categories : Transport Aircraft
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE