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Modelling the reduction of installed jet noise by using swept trailing edges

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Jet noise still dominates aircraft noise during take-off. With the aim of reducing jet noise and increasing engine efficiency, modern aircraft engines grow increasingly large. However, the increasingly large engine diameter leads to an increase of jet noise, which is commonly known as installed jet noise. Previous experiments have shown that using an aircraft wing with a swept trailing edge reduces installed jet noise. However, its mechanism remains to be known and its modelling heavily relies on numerical procedures. In this talk, I will present a robust and efficient semi-analytical model that is newly developed to model the sound due to the scattering of instability waves by an aircraft wing with a swept trailing edge. The model is based on the Schwartzchild method and the Amiet’s approach is used to obtain the far-field sound. The model can correctly predict both the reduction in installed jet noise and the change to directivity patterns observed in experiments due to the use of swept wings. It is found that the principle physical mechanism of sound reduction is the destructive interference effect. It is concluded that in order to obtain an effective noise reduction, both the span and the swept angle of the wing have to be large.

This talk is part of the Waves Group (DAMTP) series.

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