航空学报2025，Vol.46Issue(24)：66-79,14.DOI:10.7527/S1000-6893.2025.32072
直升机全机气动噪声特性风洞试验
Wind tunnel tests of aeroacoustic characteristic for helicopter aircraft model
摘要
Abstract
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 configu-rations.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 con-ducting aeroacoustic wind tunnel tests on main rotor/fuselage configurations,the impact of parameters such as ad-vance 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 aero-acoustic 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 configura-tions,and in forward flight,the thrust coefficient primarily affects low-and mid-frequency noise,whereas under de-scent 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).关键词
直升机/气动噪声/全机构型/部件影响/风洞试验Key words
helicopter/aeroacoustics/aircraft configuration/components influence/wind tunnel test分类
航空航天引用本文复制引用
LIANG Yong,ZHANG Weiguo,CHE Binghui,YUAN Honggang,WEI Chunhua,YANG Ningmeng..直升机全机气动噪声特性风洞试验[J].航空学报,2025,46(24):66-79,14.基金项目
省部级项目 Provincial and Ministerial Level Project （）
