Journal of Jilin University(Engineering and Technology Edition) ›› 2024, Vol. 54 ›› Issue (8): 2385-2392.doi: 10.13229/j.cnki.jdxbgxb.20231300

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Experimental on self-noise control of airfoil with ridge-like structure

Wen CHENG1,2(),Cheng-chun ZHANG2,3,4(),Xiao-wei SUN3,Chun SHEN2,3,Zheng-yang WU1,2,Zheng-wu CHEN1   

  1. 1.Key Laboratory of Aerodynamic Noise Control，China Aerodynamics Research and Development Center，Mianyang 621000，China
    2.Key Laboratory of Bionics Engineering（Ministry of Education），Jilin University，Changchun 130022，China
    3.Weihai Junming Power Technology Co. ，Ltd. ，Weihai 264200，China
    4.Weihai Institute of Bionics，Jilin University，Weihai 264200，China
  • Received:2023-11-24 Online:2024-08-01 Published:2024-08-30
  • Contact: Cheng-chun ZHANG E-mail:cw2143@163.com;jluzcc@jlu.edu.cn

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Abstract:

This paper presents an experiment investigation of acoustic properties for NACA0012 airfoil at different freestream velocities with 0°and 10°angle of attack（AOA）. The acoustic wind tunnel test results show that at the freestream velocities of 30-60 m/s and AOA= 0°， the dominant noise is broadband noise， but at AOA=10°， the dominant noise is switched into tonal noise， and the tonal frequency is close to the Arbey acoustic feedback model. In order to eliminate the tonal noise of airfoil， a flow control method using a ridge-like structure to break the acoustic feedback loop is proposed， and the influence of the position and arrangement of the structure on the noise reduction performance is discussed. The results show that the closer the structure is to the leading edge of the airfoil， the more obvious the noise reduction effect is. With the increase of speed， the ridge-like structure in the back position no longer has a noise reduction effect in turn. In addition， the generation of tonal noise seems to be only related to the flow state of the pressure surface. When the flow state of the pressure surface is broken by the ridge-like structure， an effective feedback loop cannot be formed. Finally， based on the Arbey acoustic feedback theory， the differences in noise reduction performance of ridge-like structures are explored. It was found that when the ridge-like structure is located before the maximum speed point of the blade pressure surface， it can effectively intervene in the flow field to suppress the generation of monophonic noise.

Key words: flow noise control, ridge-like structure, airfoil noise experiment, airfoil tonal self-noise, acoustic feedback loop

CLC Number: 

  • TB53

Fig.1

Physical diagram of wind tunnel test and schematic diagram of microphone installation"

Fig.2

Physical diagram of leading edge/trailing edge of the airfoil and its ridge structure diagram"

Table 1

Arrangement of blade model M1~M5 with ridge-like structure"

位置M1M2M3M4M5
分布双面双面双面吸力面压力面
前缘位置0.010 25c0.131 25c0.25c0.010 25c0.010 25c
后缘位置0.962 5c0.962 5c0.962 5c0.962 5c0.962 5c

Fig.3

Noise spectrum of NACA0012 airfoil at different angles of attack"

Table 2

Primary frequency prediction results of tonal noise"

速度/模型30 m/s40 m/s50 m/s60 m/s
试验1 1251 7622 4502 812
Paterson1 0582 1352 7363 256
Arbey1 1361 7412 2562 668
Brooks1 1231 5342 0282 630

Fig.4

Model M1-M3 noise spectrum at freestream velocity of 30-60 m/s"

Fig.5

Model M4-M5 noise spectrum at freestream velocity of 30-60 m/s"

Fig.6

Distribution of Isentropic Mach number on the pressure surface and the relative position at the velocity of 30~60 m/s"

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