An aircraft aerodynamic layout using trailing edge support wings

Abstract

The invention discloses an air vehicle aerodynamic configuration with two trailing edge supporting wings. The supporting wings are installed below trailing edges of main wings at the two sides of a fuselage of an air vehicle. Wingtips of the supporting wings are connected to the middle parts of the trailing edges of the wings through connection sections. Wing roots of the supporting wings are connected to the fuselage through connection sections. The relative positions of the supporting wings and the main wings are reasonably designed. In a main wing cross section and a supporting wing cross section which are truncated by air flowing to a vertical plane in wingspans of the support wings upwardly during the flying process, the vertical distance between the centroids is a% of the chord length of the cross section of the main wing, wherein a is a constant value from 10 to 40; and meanwhile, the overlapping length of projections of the chord lines of the main wing cross section and the supporting wing cross section on a horizontal plane is b% of the chord length of the cross section of the main wing, wherein b is a constant value from 0 to 15. The aerodynamic configuration increases the total lift-drag ratio and achieves better aerodynamic performances, and also improves the rigidity of large-span-chord ratio wings and improves the total structural efficiency of the air vehicle.

Description

technical field [0001] The invention belongs to the field of aircraft aerodynamic layout design, in particular to an aircraft aerodynamic layout adopting trailing edge support wings. Background technique [0002] The pursuit of a high lift-to-drag ratio has always been one of the main goals of aeronautical vehicle design. For fixed-wing aircraft with subsonic conventional layout, since the wing is its main lift component, in order to obtain a higher lift-to-drag ratio during design, the method of increasing the aspect ratio of the wing is usually adopted. The advantage of a wing with a large aspect ratio is that when the flying speed of the aircraft is low, for a wing with the same lift surface area, the use of a larger aspect ratio is beneficial to reduce the induced drag of the wing, so as to obtain a higher lift-to-drag ratio. [0003] However, since the span length of a large aspect ratio wing is much larger than the thickness and chord length of the wing, there may be...

AI Technical Summary

Problems solved by technology

However, the added support truss will cause the overall lift-to-drag ratio of the aircraft to decrease, reducing its aerodynamic efficiency

Although the wing and support truss have been optimized by the airfoil design, it can make up for a certain amount of aerodynamic loss, but according to the design experience of biplane aircraft, the aerodynamic efficiency is still relatively low if the lifting surface is arranged directly under the single wing

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