基于声学风洞的麦克风阵列测试技术应用研究  

Application investigation of microphone array measuring and testing technique in anechoic wind tunnel

作　　者：陈正武[1] 王勋年[1] 李征初[1] 刘志涛[1] 崔红芳[1] 

机构地区：[1]中国空气动力研究与发展中心、空气动力学国家重点实验室,四川绵阳621000

出　　处：《实验流体力学》2012年第3期84-90,共7页Journal of Experiments in Fluid Mechanics

基　　金：空气动力学国家重点实验室基金(SKLA2009A0103)

摘　　要：根据声学风洞气动噪声试验研究的需求,介绍了一种适用于声学风洞试验的麦克风阵列测试技术,并针对声学风洞的特点,利用风洞射流剪切层修正方法,提高了麦克风阵列识别声源的精准度。通过数值仿真和在0.55m×0.4m声学风洞的试验研究,验证了麦克风阵列测试系统和麦克风阵列数据处理方法识别声源的能力。研究结果表明所采用的麦克风阵列测试技术可用于声学风洞试验。最后还采用36通道的麦克风阵列在0.55m×0.4m声学风洞开展了NACA23018翼型气动噪声试验研究,试验明显地观察到翼型后缘噪声,获得不同迎角下翼型的噪声特性。According to the need of aerodynamic noise experimental investigation in anechoic wind tunnel, the microphone array measuring and testing technique is introduced. Based on the characteristic of anechoic wind tunnel, the correction method of shear layer in anechoic wind tun- nel is used, which improves the measuring precision of microphone array. Numerical simulation and test in 0.55m× 0.4m anechoic wind are conducted, which validate source identification capa- bility of microphone array system and data-processing method. The result indicates microphone array measuring and testing technique in this paper can be used for the testing in anechoic wind. The aerodynamic noise test for NACA23018 airfoil is put in practice. The test result shows that the trailing edge （TE） noise is observed clearly, and the aerodynamic noise characteristic of NA- CA23018 airfoil is obtained at different attack angles.

关 键 词：麦克风阵列 气动噪声 声学风洞 波束成形 翼型试验 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]