Self-adaptive adjustable low-resistance fairing

Abstract

The invention belongs to the technical field of airplane design, and relates to a self-adaptive adjustable low-resistance fairing, which comprises a fairing head part, a fairing back part, a plane body surface, a through hole, a coiled spring, a fixed sliding rail, a front end plate and a back sliding end plate. According to the invention, the conventional fairing is segmented, a set of simple flexible mechanism is added in a superposition form in the fairing, and the slenderness ratio of the fairing can be automatically changed according to the front and back pressure difference of the fairing, so that a wetted area is small and frictional drag is small when an airplane flies at a low speed, the slenderness ratio is suitable and the pressure drag is small when the airplane flies at a high speed, and the drag characteristics of the airplane at each flying speed are improved. The self-adaptive adjustable low-resistance fairing disclosed by the invention can be balanced between the pressure drag and frictional drag, the shape of the fairing can be self-adaptively changed according to the flying speed, flow separation on the fairing under a high-speed condition is restrained, and the vortex intensity at the tail part of the fairing is improved, so that the differential pressure between the front and the back of the fairing is reduced and the airplane flight resistance is reduced.

Description

technical field [0001] The invention belongs to the technical field of aircraft design and relates to an adaptive adjustable low-resistance fairing. Background technique [0002] Widely adopted by existing subsonic aircraft figure 1 , figure 2 The shape of the fairing shown to reduce the flight drag of the aircraft. The fairing is generally arranged in the direction of flow, with a raindrop-shaped head and a wedge-shaped tail. The airflow diffusion angle at the tail is generally about 10 degrees. This kind of fairing can reduce the pressure difference resistance well within a certain speed range, but When the flight speed increases, after reaching a certain speed, the airflow on the fairing will separate to form a turbulent flow area at the tail, that is, a vortex. The direction is backward, which is the backward differential pressure resistance. The slenderness ratio of this fixed fairing is constant, and the drag reduction advantage is limited to a certain speed range...

AI Technical Summary

Problems solved by technology

According to the aerodynamic characteristics of the fairing, a good fairing hopes that the slenderness ratio can be adjusted according to the flight speed of the aircraft to avoid the appearance of the tail vortex area, but the fairing of the existing aircraft does not have this feature

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