摘要
增升装置噪声是大型客机起降阶段总体噪声水平的重要组成部分。本文综述分析了增升装置噪声机理与噪声控制方法,指出了当前增升装置噪声研究中存在的几个关键难题。开展了高可靠性大涡模拟数值计算,利用相平均、本征正交分解、动态模态分解和相关性分析等方法,对缝翼噪声、襟翼尾缘噪声和襟翼侧缘噪声机理进行了深入研究,增强了对增升装置噪声机理的认识,研究结果有助于指导高效噪声控制方法设计。
High-lift device noise has been identified as a major noise source during aircraft approach and landing.Reviews on the noise generation mechanism and noise control methods of the high-lift device noise are conducted.Challenges in understanding the physical mechanism of the noise generation and implementing effective noise control has been pointed out.We performed high-fidelity large-eddy simulations for flow past the slat,flap trailing-edge and flap side-edge separately.Based on phase-averaging analysis,proper orthogonal decomposition（POD）,dynamic mode decomposition（DMD）,and two-point correlations,we increase insights on the underlying physics of the high-lift device noise.The results are expected to guide the design of high efficient noise control approaches.
作者
李伟鹏
LI Weipeng(School of Aeronautics and Astronautics, Shanghai Jiaotong University, Shanghai 200240, China)
出处
《空气动力学学报》
CSCD
北大核心
2018年第3期372-384,409,共14页
Acta Aerodynamica Sinica
基金
国家自然科学基金(11772194)
国家"973"课题(2014CB744802
2014CB744804)
关键词
增升装置噪声
噪声机理
噪声控制
high- lift device noise
noise generation mechanism
noise control methods
