초록 ▼

Modifications to a jet aircraft of the type having aft fuselage-mounted engine nacelles overlapping trailing edge portions of the aircraft\s wings, wherein a channel area defined by the fuselage, wing, pylon and attached nacelle is shaped to prevent air flowing therethrough from forming a shock wave

Modifications to a jet aircraft of the type having aft fuselage-mounted engine nacelles overlapping trailing edge portions of the aircraft\s wings, wherein a channel area defined by the fuselage, wing, pylon and attached nacelle is shaped to prevent air flowing therethrough from forming a shock wave during flight operation in the transonic regime, resulting in significant drag reduction as compared to an unmodified jet aircraft of a similar type. Further modifications to the jet aircraft\s wings provide additional lift while significantly reducing drag as compared to a similar, unmodified aircraft. The present invention is particularly adaptable for use with Gates Learjet type aircraft, especially Models 23, 24, 25 and other models having similar nacelle, pylon and inboard wing arrangements.

대표청구항 ▼

In a jet aircraft of the type having aft fuselage-mounted engine nacelles partially overlapping trailing edge portions of the aircraft\s wings, said jet aircraft being capable of flight in the transonic regime and including a channel on either side of the aircraft defined by said trailing edge porti

In a jet aircraft of the type having aft fuselage-mounted engine nacelles partially overlapping trailing edge portions of the aircraft\s wings, said jet aircraft being capable of flight in the transonic regime and including a channel on either side of the aircraft defined by said trailing edge portion of said wing, the aircraft fuselage, a pylon support assembly extending between said fuselage and said nacelle, a surface of said nacelle overlapping said wing, and an imaginary plane of symmetry extending from a lower-most outer surface of said nacelle into perpendicular contact with said wing, the improvement comprising: channel means having an area ratio of cross-sectional area at the channel exit to the minimum cross-sectional area at a position within said channel, said area ratio being less than or equal to 1:1.065 for preventing the formation of shock waves in said channel during transonic flight of said aircraft.