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| Numerical study of airfoil tonal noise based on LBM-LES |
| Received:August 26, 2018 Revised:November 03, 2018 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7511/jslx20180826002 |
| KeyWord:LBM-LES medium and low Reynolds numbers tonal noise airfoil direct calculation |
| Author | Institution |
| 冯欢欢 |
南昌航空大学 飞行器工程学院, 南昌 |
| 刘勇 |
南昌航空大学 飞行器工程学院, 南昌 |
| 王琦 |
南昌航空大学 飞行器工程学院, 南昌 |
| 邹森 |
南昌航空大学 飞行器工程学院, 南昌 |
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| Abstract: |
| Based on the LBM-LES method,the direct calculation of NACA0012 airfoil tonal noise at moderate and low Reynolds numbers are performed.The effects of different angles of attack and Reynolds numbers on tone noise were studied.The computation results indicate that the acoustic source of the airfoil is mainly located at the separation zone and the trailing edge of the airfoil.The acoustic radiation characteristics at different angles of attack and Reynolds number have the characteristics of the dipole acoustic field.The increase of the angle of attack will enlarge vortexes and raise turbulence intensity,and the acoustic source area of the suction surface will move forward.The sound pressure level spectrum analysis shows that the tonal noise gradually disappears and the noise spectrum finally becomes broadband as the angle of attack increases.As the Reynolds number increases,the trailing edge pressure pulsation increases.The primary frequency in the sound pressure level spectrum increases with the increase of the Reynolds number,and conforms to the power law relationship of the Paterson formula.In addition,the spectral characteristics of the sound pressure level show a tendency to change from discrete to broadband as the Reynolds number increases. |
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