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.
出处
《实验流体力学》
EI
CAS
CSCD
北大核心
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)
关键词
麦克风阵列
气动噪声
声学风洞
波束成形
翼型试验
microphone array
aerodynamic noise
anechoic wind tunnel
beamforming
airfoil test
