Purpose

This paper aims to assess the aeroacoustic and aerodynamic performance of a morphing airfoil with a flexible trailing edge (FTE). The objective is to make a comparison of the aerodynamic noise characteristics between the conventional airfoil with a flap and morphing airfoil and analyse the noise reduction mechanisms of the morphing airfoil.

Design/methodology/approach

The computational fluid dynamic method was used to calculate the aerodynamic coefficients of morphing airfoil and the Ffowcs-Williams and Hawking’s acoustic analogy methods were performed to predict the far-field noise of different airfoils.

Findings

Results show that compared with the conventional airfoil, the morphing airfoil can generate higher lift and lower noise, but a greater drag. Additionally, the noise caused by the one-unit lift of the morphing airfoil is significantly lower than that of the conventional airfoil. For the morphing airfoil, the shedding vortex in the trailing edge was the main noise resource. As the angle of attack (AoA) increases, the overall sound pressure level of the morphing airfoil increases significantly. With the increase of the trailing edge deflection angle, the amplitude and the period of sound pressure of the morning airfoil fluctuation increase.

Practical implications

Presented results could be very useful during designing the morphing airfoil with FTE, which has significant advantages in aerodynamic efficiency and aeroacoustic performance.

Originality/value

This paper presents the aerodynamic and aeroacoustic characteristics of the morphing airfoil. The effect of trailing edge deflection angle and AoA on morphing airfoil was investigated. In the future, using a morphing airfoil instead of a traditional flap can reduce the aircraft`s fuel consumption and noise pollution.

中文翻译：

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变形翼型的气动声学和气动特性

目的

本文旨在评估具有柔性后缘 (FTE) 的变形翼型的气动声学和气动性能。目的是比较带襟翼的常规翼型与变形翼型的气动噪声特性，分析变形翼型的降噪机理。

设计/方法/方法

采用计算流体动力学方法计算变形翼型的气动系数，采用Ffowcs-Williams和Hawking的声学类比方法预测不同翼型的远场噪声。

发现

结果表明，与常规翼型相比，变形翼型能产生更高的升力和更低的噪声，但产生更大的阻力。此外，变形翼型的单位升力引起的噪声明显低于常规翼型。对于变形翼型，后缘的脱落涡是主要的噪声源。随着迎角 (AoA) 的增加，变形翼型的整体声压级显着增加。随着后缘偏转角的增加，晨间翼型波动的声压幅度和周期增加。

实际影响

所呈现的结果在使用 FTE 设计变形翼型时非常有用，它在空气动力学效率和气动声学性能方面具有显着优势。

原创性/价值

本文介绍了变形翼型的气动和气动声学特性。研究了后缘偏转角和迎角对变形翼型的影响。未来，使用变形翼型代替传统襟翼可以减少飞机的油耗和噪音污染。