An analytic solution for gust-aerofoil interaction noise including effects of geometry
An analytic solution for gust-aerofoil interaction noise including effects of geometry
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DOI：
10.1093/imamat/hxw038
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发表时间：
2016-09
影响因子：
1.2
通讯作者：
Lorna J. Ayton
中科院分区：
文献类型：
--
作者：
Lorna J. Ayton
本文给出了具有厚度、弯度和攻角的翼型的阵风-翼型干扰声的解析解。该模型基于定常亚音速流的欧拉方程线性化，是以前考虑限制性翼型几何形状的工作的扩展。只考虑高频事件阵风。翼型厚度、弯度和迎角应使经过翼型的定常流被看作是对均匀流的一个小扰动。匹配渐近展开的方法用于识别翼型周围的区域，其中不同的过程控制声音的产生或传播。翼型前缘和后缘的关键局部区域决定噪声的产生，而沿着刚性翼型表面的过渡区域和远离表面的外部区域在声音传播中起关键作用。沿着改变前缘半径的影响，讨论了改变厚度和外倾角的影响。
An analytic solution is obtained for the sound generated by gust-aerofoil interaction for aerofoils with thickness, camber and angle of attack. The model is based on the linearization of the Euler equations about a steady subsonic flow, and is an extension of previous work which considered restrictive aerofoil geometries. Only high-frequency incident gusts are considered. The aerofoil thickness, camber and angle of attack are such that the steady flow past the aerofoil is seen as a small perturbation to uniform flow. The method of matched asymptotic expansions is used to identify regions around the aerofoil where different processes govern the generation or propagation of sound. Key local regions at the leading and trailing edges of the aerofoil determine the generation of noise whilst transition regions along the rigid aerofoil surface, and outer regions away from the surface play key roles in the propagation of sound. The effects of varying thickness and camber angle are discussed, along with the effects of varying the radius of the leading edge.