| 摘要 |
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.
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