直升机全机气动噪声特性风洞试验
收稿日期: 2025-04-03
修回日期: 2025-05-04
录用日期: 2025-05-30
网络出版日期: 2025-06-20
基金资助
省部级项目
Wind tunnel tests of aeroacoustic characteristic for helicopter aircraft model
Received date: 2025-04-03
Revised date: 2025-05-04
Accepted date: 2025-05-30
Online published: 2025-06-20
Supported by
Provincial and Ministerial Level Project
基于声学风洞开展直升机全机气动噪声特性研究，是评估直升机气动噪声水平的一种有效手段。针对直升机全机构型开展气动噪声试验，系统研究了直升机全机及不同部件组合的气动噪声特性。首先，通过对比国内外不同风洞性能数据，评估了试验风洞的信噪比，确保了试验结果的准确性；其次，针对旋翼/机身构型开展了不同飞行工况下的气动噪声风洞试验，研究了前进比、升力系数、总距和轴倾角等参数对噪声频谱特性、倍频噪声幅值和总声压级的影响；最后，研究了尾桨对全机噪声辐射特性的影响，并对全机噪声特征影响参数进行了分析。研究结果表明，悬停和前飞时尾桨会导致全机中高频段噪声增加；轴倾角对不同构型的噪声特性影响较大，前飞状态下升力系数主要对低频段和中频段噪声产生影响，斜下降状态下升力系数主要对中高频段噪声产生明显影响；尾桨主要在悬停和水平前飞状态下对全机噪声有增强作用，在斜下降状态下由于桨-涡干扰（BVI）的强噪声覆盖作用，尾桨噪声对全机噪声大小和辐射特性的影响相对较小。
梁勇 , 张卫国 , 车兵辉 , 袁红刚 , 魏春华 , 杨柠檬 . 直升机全机气动噪声特性风洞试验[J]. 航空学报, 2025 , 46(24) : 132072 -132072 . DOI: 10.7527/S1000-6893.2025.32072
Conducting research on the aeroacoustic characteristics of helicopters in a wind tunnel is an effective method for evaluating helicopter noise levels. Aeroacoustic tests were conducted on the full helicopter configuration， systematically investigating the noise characteristics of the complete aircraft and various component assembly configurations. Firstly， to ensure the accuracy of the test results， the precision of the model control and ratio of the signal and noise were validated by comparing the test data from different wind tunnels at home and abroad. Secondly， by conducting aeroacoustic wind tunnel tests on main rotor/fuselage configurations， the impact of parameters such as advance ratio， thrust coefficient， collective pitch angle， and shaft tilt angle on noise spectrum characteristics， harmonic noise amplitude， and overall sound pressure level was analyzed. Finally， the contribution of the tail rotor to the aeroacoustic performance of the full configuration was also analyzed， followed by a parametric analysis of the dominant noise contributors. The research results indicate that in the hovering state and forward flight， the tail rotor increases mid-to-high-frequency noise. The shaft tilt angle significantly impacts noise characteristics across different configurations， and in forward flight， the thrust coefficient primarily affects low- and mid-frequency noise， whereas under descent flight condition， its influence shifts to mid-and high-frequency noise. The tail rotor enhances overall noise in hover and level forward flight. However， under descent flight conditions， its contribution becomes less pronounced due to the dominant noise generated by Blade-Vortex Interaction （BVI）.
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