Aerodynamic layout of aircraft with blended wing body

Abstract

The invention discloses an aerodynamic layout of an aircraft with a blended wing body and belongs to the technical field of aircrafts. The aerodynamic layout is designed for solving the problems that an existing aircraft with a blended wing body is insufficient in lift force and large in flight drag. The aerodynamic layout of the aircraft with the blended wing body involves the blended wing body and a rear wing; a fuselage and a wing of the blended wing body are blended to constitute a front wing; the rear wing is a horizontal tail, and the two sides of the horizontal tail are connected with the two sides of the front wing through connecting parts respectively. On the basis of wing and fuselage blending, the horizontal tail is added to serve as the rear wing so that the lift force of the aircraft with the blended wing body can be increased; in addition, the arrangement area of a high-lift device and the arrangement area of an operating device are increased so that the maximum lift coefficient can be increased and the take-off and landing performance of the aircraft can be improved.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to an aerodynamic layout of a wing-body fusion aircraft. Background technique [0002] Economy is an important factor considered in the design of passenger aircraft. Aircraft designers pursue how to use less energy consumption to obtain greater lift resistance, longer range and more load on the basis of safety, comfort and environmental protection. passenger volume. The future large passenger aircraft puts forward higher requirements on the aerodynamic layout, and the conventional layout must increase the wing area and expand the loading space of the fuselage in order to increase the lift-to-drag ratio and increase the range. Aerodynamics bring many challenges, resulting in difficulties such as reduced weight efficiency and series development. Therefore, the innovation of aerodynamic layout plays a key role in improving the performance of large passenger aircraft. [0003] In rec...

AI Technical Summary

Problems solved by technology

[0004] 1. The BWB layout does not have a slender fuselage with a conventional layout, and the horizontal tail cannot be arranged. The tail edge must be used for trimming, and the control surface is arranged on the trailing edge of the wing; since the control surface is arranged on the trailing edge of the wing, the area of ​​the lifting device is large. Smaller than the conventional layout, resulting in a decrease in the maximum lift coefficient and affecting take-off and landing performance;

[0005] 2. The tail arm of the BWB layout is relatively short. In order to meet the requirements of the trim moment, it is necessary to arrange a larger control surface on the trailing edge of the wing, but this will generate more negative lift and reduce the lift of the whole aircraft;

[0006] 3. In order to consider the loading space requirements, the thickness of the central fuselage is relatively large. When flying at high subsonic speeds, large wave resistance will inevitably be generated, which increases the resistance of the aircraft

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