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第 41 卷 第 6 期                                                                       Vol. 41, No. 6
             2022 年 11 月                         Journal of Applied Acoustics                 November, 2022

             ⋄ 研究报告 ⋄



                 机体表面湍流边界层噪声特性及预测方法研究





                                   宋 晓     †   Cyrille Breard      孙一峰 田嘉劲


                                                (上海飞机设计研究院      上海   201210)

                摘要：湍流边界层噪声是飞机巡航过程中的主要外部噪声源，对舱内噪声水平的影响尤为重要。因此，对飞机
                机体表面湍流边界层噪声的研究具有重要意义。该文通过试验获得了某型民机巡航过程中的湍流边界层噪
                声，试飞工况为 35000 ft/0.78、35000 ft/0.7、25000 ft/0.67、15000 ft/0.66。对实测数据进行分析，发现湍流边
                界层噪声与动压、边界层厚度等参数有关。同时，利用计算流体力学的方法得到了飞机机体表面的压力分布，
                并分析了压力梯度对湍流边界层噪声的影响。最后，基于工程预测方法对湍流边界层噪声进行了预测，对于不
                存在逆压梯度的区域，预测结果与试验结果吻合较好，仅部分频段存在一定偏差。通过对模型的参数进行优
                化，改善了预测结果。
                关键词：湍流边界层；压力脉动；工程预测
                中图法分类号: V2           文献标识码: A          文章编号: 1000-310X(2022)06-0884-07
                DOI: 10.11684/j.issn.1000-310X.2022.06.005





               Turbulent boundary layer noise characteristics and prediction method on the
                                                   airframe surface



                                  SONG Xiao Cyrille Breard SUN Yifeng       TIAN Jiajin

                                 (Shanghai Aircraft Design and Research Institute, Shanghai 201210, China)

                 Abstract: Turbulent boundary layer noise is the main external noise source during aircraft cruise, which has a
                 particularly important impact on the noise level in the cabin. Therefore, it is of great significance to study the
                 turbulent boundary layer noise on the airframe surface. In this paper, the turbulent boundary layer noise of a
                 civil aircraft during cruise is obtained experimentally. The flight test conditions are 35000 ft/0.78, 35000 ft/0.7,
                 25000 ft/0.67 and 15000 ft/0.66. By analyzing the measured data, it is found that the turbulent boundary
                 layer noise is related to parameters such as dynamic pressure and boundary layer thickness. At the same
                 time, the pressure distribution on the aircraft body surface is obtained by using the method of computational
                 fluid dynamics, and the influence of pressure gradient on turbulent boundary layer noise is analyzed. Finally,
                 the turbulent boundary layer noise is predicted based on the engineering prediction method. For the region
                 where there is no inverse pressure gradient, the prediction results are in good agreement with the experimental
                 results, and there is a certain deviation in some frequency bands. By optimizing the parameters of the model,
                 the prediction results are improved.
                 Keywords: Turbulent boundary layer; Pressure fluctuation; Engineering prediction

             2021-09-23 收稿; 2021-12-22 定稿
             作者简介: 宋晓 (1990– ), 男, 河南郑州人, 硕士, 研究方向: 航空声学。
             † 通信作者 E-mail: songxiao@comac.cc
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