不同前缘翼型气动和噪声特性对比研究  

Research on Aerodynamic and Aeroacoustic Characteristics of Different Airfoil

作　　者：宋妙妍 陈宝[1,2] 王普缘 李春鹏[3] Song Miaoyan;Chen Bao;Wang Puyuan;Li Chunpeng(Aerodynamic Noise and Control Lab of Heilongjiang Province,AVIC Aerodynamics Research Institute,Harbin 150001,China;Low Speed High Reynolds Number Aeronautical Key Laboratory,AVIC Aerodynamics Research Institute,Harbin 150001,China;High Speed HighReynolds Number Aeronautical Key Laboratory,AVIC Aerodynamics Research Institute,Shenyang 110034,China)

机构地区：[1]中国航空工业空气动力研究院黑龙江省空气动力噪声及其控制重点实验室,黑龙江哈尔滨150001 [2]中国航空工业空气动力研究院低速高雷诺数航空科技重点实验室,黑龙江哈尔滨150001 [3]中国航空工业空气动力研究院高速高雷诺数气动力航空科技重点实验室,辽宁沈阳110034

出　　处：《气动研究与试验》2024年第4期87-96,共10页Aerodynamic Research & Experiment

摘　　要：多段翼增升装置的噪声与其前缘缝翼有很大的关系,凹腔内存在的涡-涡干扰、剪切层/壁面冲击等非定常现象以及缝翼尾缘的涡脱落是影响增升装置噪声的主要原因之一。利用定常得到的稳定场采用宽频噪声源方法分析翼型周围噪声源强度,然后使用分离涡方法(DES)结合FW-H声类比方法研究前缘下垂和前缘缝翼模型在迎角变化时的气动与噪声特性,研究发现前缘采用下垂的形式在一定迎角范围内能获得较好的降噪效果,并且能够提升翼型的气动性能。Aerodynamic noise of multi-element airfoils has large relationship with its slat,the unsteady phenomenon and the vortex shedding are the main noise source,such as the interaction between vortex and vortex,and the impact on the shear layer and wall.Using the flow field caused by steady simulation,acoustic source intensity is analyzed by Broadband noise source.The effect of leading-edge droop nose and slats with different angles of attack on noise and force is analyzed based on Detached Eddy Simulation(DES)and Ffowcs Wiliams and Hawkings(FW-H).The results show that leading edge droop nose has positive effect on noise suppression and aerodynamic characteristics in some angles of attack,and also enhance the aerodynamics of airfoils.

关 键 词：前缘缝翼 前缘下垂 气动噪声 气动力 DES 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]