Hypersonic velocity waverider double-wing aerodynamic layout

Abstract

The invention discloses a hypersonic velocity waverider double-wing aerodynamic layout, and double wings are mounted in the middle of a machine body and comprise an upper layer wing and a lower layer wing which are mounted symmetrically up and down; waverider design is integrated into selection of airfoil parameters of the upper layer wing and the lower layer wing, and the defects that the current wave-rider volume fraction is low and the wing body combination lift-drag ratio is not high can be effectively made up; the lifting surface area can be effectively increased, the chord length is not required to be increased while an air vehicle acquires an enough lifting surface, and accordingly, the stability and the manoeuvrability of the wide velocity area of the flight vehicle are improved. At the same time, the distance of the leading edges of the double wings is designed, so that unfavourable interference cannot occur between the two wings under the cruise working condition of the flight vehicle.

Description

technical field [0001] The invention belongs to the field of aerodynamic layout design of a hypersonic aircraft, and in particular relates to the concept and principle of an aerodynamic layout of waveriding wings. Background technique [0002] Since the lift-to-drag ratio of an aircraft is directly related to its range, energy consumption, and economy, the lift-to-drag ratio is usually used as an important indicator to measure the aerodynamic performance of an aircraft, and the pursuit of a high lift-to-drag ratio has always been one of the main goals of aircraft design. The waverider configuration is the preferred solution to obtain a high lift-to-drag ratio in hypersonic flight. It can attach all the shock waves generated on the lower surface to the leading edge, and use the high-pressure gas behind the wave on the lower surface to obtain a higher lift-to-drag ratio. [0003] Research shows that the object surface angle of the lower surface of the waverider is the decisive...

AI Technical Summary

Problems solved by technology

[0004] One is the limitation of the length of the lift surface by factors such as the size of the launch tube / frame;

[0005] The second is the limitation of the chord length of the lift surface by the stability characteristics of the wide speed range

Therefore, this concept will undoubtedly make the lifting surface lose its main function, and the Busemann supersonic biplane concept is obviously not suitable for direct application to the design of the lifting surface of hypersonic aircraft

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