초록 ▼

An apparatus and method are provided for reducing the drag of an aircraft wing. Many modern high speed aircraft have a low aspect ratio wing generating significant induced drag. The invention provides a drag reduction system, which is made up of a high aspect ratio supplementary wing connected to th

An apparatus and method are provided for reducing the drag of an aircraft wing. Many modern high speed aircraft have a low aspect ratio wing generating significant induced drag. The invention provides a drag reduction system, which is made up of a high aspect ratio supplementary wing connected to the fuselage by a streamlined fuselage connection, and at least two struts connecting the supplementary wing to the main wing. The drag reduction system is capable of reducing the total drag of a modern high speed, high altitude aircraft with a low aspect ratio cantilevered wing, by at least 29.1%. At least 65% of the total lift of the aircraft can be provided by the supplementary wing. The main wing then provides structural strength to transfer lifting loads to the fuselage of the aircraft, and for this purpose, the main wing and interconnections for the supplementary wing can be designed with this structural function in mind.

대표청구항 ▼

1. An aircraft comprising: a body; a supplementary wing comprising two wing, sections extending outwardly on either side of the body, to provide lift for the body; and a wing support structure for the supplementary wing extending between the body and the supplementary wing, wherein the supplementary

1. An aircraft comprising: a body; a supplementary wing comprising two wing, sections extending outwardly on either side of the body, to provide lift for the body; and a wing support structure for the supplementary wing extending between the body and the supplementary wing, wherein the supplementary wing is configured to reduce induced drag and the supplementary wing by itself has insufficient strength to support the aircraft, wherein the wing support structure comprises a main wing and provides additional strength to withstand loads applied to the supplementary wing by lift forces at least, wherein the main wing extends outwardly from the body spaced from the supplementary wing and the wing support structure includes at least two connections between the main wing and the supplementary wing transferring loads between the supplementary wing and the main wing, wherein the main wing has a low aspect ratio and the supplementary wing has a high aspect ratio, and wherein the main and supplementary wings are configurable to provide the supplementary wing with a higher lift coefficient than the main wing, thereby to provide an overall drag reduction.