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Aerodynamic configuration of aircraft

An aerodynamic layout and aircraft technology, applied in the direction of wing shape and other directions, can solve the problems of low speed and difficult trim of aircraft, and achieve the effect of improving flight speed and solving difficulty in trim.

Inactive Publication Date: 2012-12-19
JIANGXI HONGDU AVIATION IND GRP
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AI Technical Summary

Problems solved by technology

[0008] In order to solve the problems of low aircraft speed and difficult trimming in the above-mentioned flying wing layout, an improved aircraft aerodynamic layout is proposed

Method used

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  • Aerodynamic configuration of aircraft
  • Aerodynamic configuration of aircraft

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Embodiment 1

[0017] The aerodynamic layout of a certain type of machine is that the outer wing section 1 adopts a laminar flow airfoil with a small bow moment and a maximum thickness of 8%, the outer wing sweep angle 5 is 25°, the aspect ratio is 9, and the trapezoidal ratio is 2.27; the inner wing section adopts The laminar flow airfoil with a maximum thickness of 10% and a small nose-down moment has a sweep angle of 42°, an aspect ratio of 1.75, and a trapezoidal ratio of 1.21; the inner wing section 2 is connected with the fuselage 1 to realize wing-body fusion. The moment balance point of the aerodynamic layout scheme appears at an angle of attack of 3°. When the angle of attack is 3°, the lift coefficient of the whole machine is 0.244, the maximum lift-to-drag ratio is greater than 17, and the maximum Mach number is 0.86; it shows that the aerodynamic layout scheme basically achieves Self-trimming means that the angle of attack corresponding to the maximum lift-to-drag ratio is the bal...

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Abstract

The invention relates to the technical field of aerodynamic configuration design of aircrafts, in particular to an aerodynamic configuration of an aircraft. The aerodynamic configuration of the aircraft comprises an aircraft body (3), outer wing sections (1) and inner wing sections, and is characterized in that the surfaces of the outer wing sections (1) and the inner wing sections (2) are laminar flow airfoils; the inner wing sections (2) are wing-body transition sections, adopt back-swept wings with a moderate sweep back angle and a small span-chord ratio and are connected with the aircraft body; the wings and the aircraft body are fused together; and the outer wing sections (1) adopt forward-swept wings with a moderate sweep forward angle and a moderate span-chord ratio. Due to the aerodynamic configuration of the aircraft, not only can the requirement on high-altitude long-endurance high-subsonic-speed cruise of the aircraft be satisfied, but also the flight speed is improved and the problem of trimming difficulty is solved.

Description

technical field [0001] The invention relates to the technical field of aircraft aerodynamic layout design. Background technique [0002] Aircraft is the crystallization of contemporary advanced science and cutting-edge technology. It is a complex system engineering, in which aerodynamic layout design is the top priority, which is directly related to the comprehensive use efficiency of the aircraft. [0003] The wing is the most important aerodynamic component in the aircraft component, and it is the main component for the aircraft to generate aerodynamic lift. The forward-swept wing is a wing shape design of the oblique-swept wing. Like the swept-back wing, it can increase the Mach number of drag divergence and improve the speed performance of the aircraft. The forward-swept wing generates inboard airflow to the wing root, which loads the wing root, and the load distribution of the wing along the span direction is more reasonable than that of the swept-back wing. For examp...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/10
Inventor 符松海卢森李鹏飞胡睿辛荣提冷智辉沈亮
Owner JIANGXI HONGDU AVIATION IND GRP
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