Ice accretion changes the shape of the airplane aerodynamic surface, resulting in not only the degradation of aerodynamic performance but also the variation of the aeroacoustic characteristics. In order to explore the effect of the ice accretion on the aerodynamic noise, a NACA0012 airfoil with rime ice model on the leading edge was investigated experimentally in an aeroacoustic wind tunnel using far-field microphone array measurements. Two rime ice models of different ice thickness were attached on the airfoil leading edge. The results were compared with the baseline airfoil at various airflow speeds and different angles of attack. The experiments reveal that the ice model increases the maximum far-field sound pressure level (SPL) by 9.5 dB in the frequency band of 7–25 kHz. And the averaged OASPL difference between airfoil with ice model and baseline airfoil is linear with the 1/2 power of ice thickness. Higher angle of attack results in larger increase of the noise level. Steady RANS simulation as well as large eddy simulation was also performed to uncover the mechanism of the noise increase by the rime ice model. The presence of the rime ice model altered the local flow field around the leading edge of airfoil, resulting in the variation of airfoil surface pressure fluctuation and far-field acoustic characteristics. It would enhance the noise radiation of the airfoil, which was verified by the sound power level (PWL) of airfoil with ice model. It may provide an idea to develop a novel ice detection method based on the far-field noise increment by the ice model.

积冰改变了飞机空气动力学表面的形状，不仅导致空气动力学性能的下降，而且导致空气声学特性的变化。为了探究积冰对空气动力噪声的影响，使用远场麦克风阵列测量，在空气声风洞中对前缘装有冰面冰模型的NACA0012翼型进行了实验研究。在翼型前缘上安装了两个冰厚度不同的冰霜模型。将结果与在不同气流速度和不同迎角下的基准翼型进行了比较。实验表明，冰模型在7–25 kHz频带内将最大远场声压级（SPL）提高了9.5 dB。和平均带冰模型的机翼与基准翼型之间的OASPL差异与冰厚度的1/2幂成线性关系。更大的迎角导致更大的噪声水平增加。还进行了稳定的RANS仿真以及大涡流仿真，以揭示霜冰模型增加噪声的机理。霜冰模型的存在改变了机翼前缘周围的局部流场，导致机翼表面压力波动和远场声学特性的变化。这将增强机翼的噪声辐射，这已通过带有冰模型的机翼的声功率级（PWL）进行了验证。它可能为基于冰模型的远场噪声增量开发一种新颖的冰探测方法提供一个思路。