【作者】 黄奔； 王勇； 陈鹏； 雷红胜；

【Author】 HUANG Ben;WANG Yong;CHEN Peng;LEI Hongsheng;Key Laboratory of Aerodynamic Noise Control , China Aerodynamic research and Development Center;

【机构】 中国空气动力研究与发展中心气动噪声控制重点实验室；

【摘要】 大型民用客机的噪声水平是影响其适航取证的重要指标,在飞机高速飞行时,气动噪声为最主要的噪声来源,而风洞试验是气动噪声评估及发展气动噪声抑制措施的有效手段。通过在5.5m×4m风洞开展某客机半模气动噪声试验,利用尺寸为3m×3m的麦克风阵列进行噪声测量,获得了模型的气动噪声特性及总体噪声源分布。并对该客机半模增升装置进行噪声抑制研究,发现对缝翼几何不连续位置修形可明显降低整体宽频噪声;在缝翼前缘进行加厚处理可明显抑制单频噪声的产生,且加厚0.4mm时抑制效果最佳;在缝翼后缘进行加厚处理无抑制噪声作用,反而增强了高频噪声。更多还原

【Abstract】 The noise level of large civil plane is a important index which would influence the collection of seaworthy evidence.When the plane is flying at a high speed, the aerodynamic noise is the most important noise source.So it’s necessary to study the aerodynamic noise in the wind tunnel which is an effective technique for aerodynamic noise reduction.The test of noise source distribution and spectral characteristic for a plane is carried out in the 5.5m×4m acoustic wind tunnel.The research on noise reduction for high lift showed following: The broad band noise could be inhibited resorted to modify the leading edge slats configuration.And reducing single-frequency noise by means of increasing the thickness of slat leading edge could be achieved when its thickness increase by 0.4mm.Otherwise, not only has no effect on noise suppression when increase the thickness of slat trailing edge, but it would enhance high-frequency noise.更多还原