Numerical prediction of trailing edge noise at low Reynolds number with modified trailing edges of a NACA 0015 airfoil
Global concern about high noise levels in areas near airports and wind farms has generated interest from various groups due to factors such as potential health problems and dissatisfaction among the local community. To accommodate this worthwhile plan of further reducing overall noise levels, some r...
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my.iium.irep.1091912024-05-02T05:58:46Z http://irep.iium.edu.my/109191/ Numerical prediction of trailing edge noise at low Reynolds number with modified trailing edges of a NACA 0015 airfoil Hassan, Mohamed Ibren Andan, Amelda Dianne Asrar, Waqar TL500 Aeronautics Global concern about high noise levels in areas near airports and wind farms has generated interest from various groups due to factors such as potential health problems and dissatisfaction among the local community. To accommodate this worthwhile plan of further reducing overall noise levels, some researchers are working on lowering the contribution of trailing-edge noise. The original scientific contribution of this study lies on understanding the efficiency of various trailing edge designs such as baseline, serrations, comb and comb-serrated, across different angles of attack and Reynolds numbers, while also addressing the limitations of existing geometrical models for trailing edges. The study intends to examine the performance of these different configurations, with an emphasis on their effect on acoustic responses. By utilizing large-eddy simulation and applying the Ffowcs-Williams and Hawkings models for noise prediction, an investigation was conducted to assess the impact of these trailing edge configurations on radiated noise at a low Reynolds number of 1.6× 105. The numerical predictions of lift coefficient and surface pressure fluctuations are compared and validated with a published study and experimental data, showing satisfactory results. Further analysis of these study has demonstrated that prominent peaks at lower frequencies (<103) are observed, which are identified as the characteristic frequencies. Moreover, results showed irregular broadband noise (300 - 600 Hz) with increased noise and shifting peak frequency as angle of attack rose. The serrated trailing edge design notably reduced noise levels by roughly 21 dB, especially for low frequencies. Comb-serration increased high-frequency noise by about 9 dB for angles of attack at 0, -1, and -20, and achieved a reduction of approximately 9 dB for angles of attack at 1 and 20. On the other hand, the directivity pattern showed that the maximum noise level is observed to predominantly radiate at an azimuth angle of around 90 degrees for all the cases, ranging from 900 to 2700, indicating that the majority of the source's acoustic energy is being emitted on the suction and pressure sides of the airfoil. Semarak Ilmu Publishing 2024-03-31 Article PeerReviewed application/pdf en http://irep.iium.edu.my/109191/2/109191_Numerical%20prediction%20of%20trailing%20edge%20noise.pdf application/pdf en http://irep.iium.edu.my/109191/3/109191_Numerical%20prediction%20of%20trailing%20edge%20noise_SCOPUS.pdf Hassan, Mohamed Ibren and Andan, Amelda Dianne and Asrar, Waqar (2024) Numerical prediction of trailing edge noise at low Reynolds number with modified trailing edges of a NACA 0015 airfoil. CFD Letters, 16 (8). pp. 64-94. ISSN 2180-1363 E-ISSN 2180-1363 https://semarakilmu.com.my/journals/index.php/CFD_Letters/article/view/5013 10.37934/cfdl.16.8.6494 |
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TL500 Aeronautics Hassan, Mohamed Ibren Andan, Amelda Dianne Asrar, Waqar Numerical prediction of trailing edge noise at low Reynolds number with modified trailing edges of a NACA 0015 airfoil |
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Global concern about high noise levels in areas near airports and wind farms has generated interest from various groups due to factors such as potential health problems and dissatisfaction among the local community. To accommodate this worthwhile plan of further reducing overall noise levels, some researchers are working on lowering the contribution of trailing-edge noise. The original scientific contribution of this study lies on understanding the efficiency of various trailing edge designs such as baseline, serrations, comb and comb-serrated, across different angles of attack and Reynolds numbers, while also addressing the limitations of existing geometrical models for trailing edges. The study intends to examine the performance of these different configurations, with an emphasis on their effect on acoustic responses. By utilizing large-eddy simulation and applying the Ffowcs-Williams and Hawkings models for noise prediction, an investigation was conducted to assess the impact of these trailing edge configurations on radiated noise at a low Reynolds number of 1.6× 105. The numerical predictions of lift coefficient and surface pressure fluctuations are compared and validated with a published study and experimental data, showing satisfactory results. Further analysis of these study has demonstrated that prominent peaks at lower frequencies (<103) are observed, which are identified as the characteristic frequencies. Moreover, results showed irregular broadband noise (300 - 600 Hz) with increased noise and shifting peak frequency as angle of attack rose. The serrated trailing edge design notably reduced noise levels by roughly 21 dB, especially for low frequencies. Comb-serration increased high-frequency noise by about 9 dB for angles of attack at 0, -1, and -20, and achieved a reduction of approximately 9 dB for angles of attack at 1 and 20. On the other hand, the directivity pattern showed that the maximum noise level is observed to predominantly radiate at an azimuth angle of around 90 degrees for all the cases, ranging from 900 to 2700, indicating that the majority of the source's acoustic energy is being emitted on the suction and pressure sides of the airfoil. |
format |
Article |
author |
Hassan, Mohamed Ibren Andan, Amelda Dianne Asrar, Waqar |
author_facet |
Hassan, Mohamed Ibren Andan, Amelda Dianne Asrar, Waqar |
author_sort |
Hassan, Mohamed Ibren |
title |
Numerical prediction of trailing edge noise at low Reynolds number with modified trailing edges of a NACA 0015 airfoil |
title_short |
Numerical prediction of trailing edge noise at low Reynolds number with modified trailing edges of a NACA 0015 airfoil |
title_full |
Numerical prediction of trailing edge noise at low Reynolds number with modified trailing edges of a NACA 0015 airfoil |
title_fullStr |
Numerical prediction of trailing edge noise at low Reynolds number with modified trailing edges of a NACA 0015 airfoil |
title_full_unstemmed |
Numerical prediction of trailing edge noise at low Reynolds number with modified trailing edges of a NACA 0015 airfoil |
title_sort |
numerical prediction of trailing edge noise at low reynolds number with modified trailing edges of a naca 0015 airfoil |
publisher |
Semarak Ilmu Publishing |
publishDate |
2024 |
url |
http://irep.iium.edu.my/109191/2/109191_Numerical%20prediction%20of%20trailing%20edge%20noise.pdf http://irep.iium.edu.my/109191/3/109191_Numerical%20prediction%20of%20trailing%20edge%20noise_SCOPUS.pdf http://irep.iium.edu.my/109191/ https://semarakilmu.com.my/journals/index.php/CFD_Letters/article/view/5013 |
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