5.5m×4m声学风洞在中俄民机起落架噪声特性及控制技术联合研究中的应用

Application of 5.5m × 4m aeroacoustic wind tunnel in Sino-Russia joint research collaboration on landing gear noise and its control

以中国-俄罗斯民用飞机起落架噪声特性及控制技术联合研究中所使用的5.5 m×4 m声学风洞(FL-17风洞)为例,介绍了大型声学风洞在科研工作中的应用情况。首先介绍了FL-17风洞的研制历程与各项性能指标;然后基于中俄联合研究中的大尺度起落架气动噪声风洞试验,概述了起落架噪声相关领域的研究现状,以及利用FL-17风洞开展的起落架噪声机理与控制技术方面的研究内容与成果,如试验、数值模拟和噪声预测数据库,以及基于非常规截面方法和空气幕方法的起落架降噪技术等;最后,对于大型声学风洞的科研使用给出了一些经验和建议。

Regarding applications of the large-scale aeroacoustic wind tunnel in scientific research, this paper introduces the usage of FL-17, a 5.5 m × 4 m aeroacoustic wind tunnel, in a Sino-Russia joint collaboration research project on civil aircraft landing gear noise and its control. First of all, the construction history and specifications of FL-17 wind tunnel are introduced. Then, based on the large-scale wind tunnel test of landing gear aerodynamic noise in Sino-Russia joint research, the state-of-the-art of the landing gear noise investigation was introduced, as well as the research contents and achievements of the landing gear noise and its control carried out in FL-17 wind tunnel. The discussions involve large-scale experimental studies, database of full-scale landing gear experiment, numerical simulations, prediction models, noise control using truncated cylinders and air curtains, etc. As last, some experiences and suggestions on the usage of large-scale aeroacoustic wind tunnel were provided.