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Wingtip noise control and device

A noise control and wingtip technology, applied in aircraft control, transportation and packaging, aircraft parts, etc., can solve problems such as pressure fluctuations, instability, and unstable vortex modes in the flow field at the side of the lift surface, and achieve control of the wingtip noise effect

Inactive Publication Date: 2012-07-04
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Second, the amplification of the unstable vortex mode
Both the shear layer and the instability of the vortex will cause pressure fluctuations in the flow field at the side of the lifting surface and radiate to the far field

Method used

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  • Wingtip noise control and device

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Embodiment Construction

[0025] The implementation process of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0026] A method for wingtip noise reduction control, such as figure 2 As shown in b, the method is by installing a flow control device (can be installed on the upper surface, side surface or lower surface near the wing end) at the wing end of the lifting surface such as the aircraft wing or flap; way to control the nearby flow field. When the aircraft is flying at a high angle of attack and taking off or landing, the jet flow method is used to change or weaken the large-scale unsteady vortex structure at the wing end due to the pressure difference between the upper and lower lift surfaces, so as to reduce the level of object surface and far-field pulsation pressure. In the cruising phase, the jet does not work to reduce energy consumption.

[0027] The above-mentioned flow control device can be realized by the wing cover device instal...

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Abstract

The invention discloses a wingtip noise control and a device. The method comprises the following steps that: (1) a flow control device is installed at a wingtip of a wing or a wing flap and other elevating force sides of an aircraft; (2) when the aircraft flies at high incidence and takes off or lands, the flow control device is utilized to change or weaken a large-scale unsteady wingtip vortex structure which is generated due to the differential pressure between the upper and the lower surfaces of the elevating force side through adopting a jet flow mode; during a cruising period, the flow control device does not work; and the nozzle of the flow control device adopts a sawtooth structure, the included angle of sawtooth side lines is 60-130 degrees, the sawtooth height is 2-5cm, and the sawtooth length is 0.4-0.6 time that of the chord length.

Description

technical field [0001] The invention relates to an aerodynamic noise control technology, which adopts an active control method to control the jet flow near the wing tip, destroys or reduces the large-scale eddy current field structure near the wing tip during the flight of the aircraft, and reduces the aerodynamic noise radiation of the wing tip. technical background [0002] In the past few decades, the research on aerodynamic noise has made important progress in the research on the noise reduction of aircraft propulsion system. However, modern aircraft need to achieve higher levels of noise reduction, and aircraft engines are not the only noise source to consider. Especially during the take-off and landing stages, aircraft body noise is a non-negligible component of the total aircraft noise. Among them, an important sound source in the airframe noise is located at the side end of the lift surface (such as wing, flap) of the aircraft. [0003] The physical mechanism of th...

Claims

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Application Information

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IPC IPC(8): B64C23/00
Inventor 郭欣王强冯峰
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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