Low-resistance fairing of corrugate sheath

Abstract

The invention belongs to the technical field of airplane design, and relates to a low-resistance fairing of a corrugate sheath, which is improved on a plane fairing part. The fairing consists of a fairing head part, a fairing back part, a fairing corrugate sheath, a resilient surface rubber, a plane body surface and a through hole, wherein the fairing head part is fixedly riveted or bonded on the plane body surface, the through hole is arranged at the most front end of the fairing head part, i.e. near an airflow stationary point, the through hole is communicated with an inner cavity of the fairing, the fairing corrugate sheath is arranged in the position with the biggest cross section area of the fairing, the fairing corrugate sheath is bonded between the fairing head part and the fairing back part, and the resilient surface rubber is bonded on the outer surface of a wave crest position of the corrugate sheath. The low-resistance fairing of the corrugate sheath disclosed by the invention can be balanced between pressure drag and frictional drag, the shape of the fairing is self-adaptively changed according to flight 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 plane flight resistance is reduced.

Description

Technical field: [0001] The invention belongs to the technical field of aircraft design, and relates to a corrugated sleeve low-resistance fairing improved on aircraft fairing parts. 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 of pressure is backward, which is the backward differential pressure resistance. The slenderness ratio of this fixed fairing is constant, and the drag reducti...

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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