| A boundary surrogate model for micro/nano grooved surface structure applied in turbulence flow control over airfoil |
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| 作者姓名： | Liyue WANG Cong WANG Shuyue WANG Sheng QIN Gang SUN Bo YOU Yongjian ZHONG |
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| 作者单位： | Department of Aeronautics & Astronautics,Fudan University,Shanghai 200433,China;Department of Material Science,Fudan University,Shanghai 200433,China;AECC Commercial Aircraft Engine Co.,Ltd.,Shanghai 200241,China |
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| 摘 要： | The application of grooved surface structure is an emerging and effective means in turbulence flow control. However, for a realistic configuration, the global flow field described directly by simple application of massive grids makes it unfeasible to simulate. In this paper, a boundary surrogate model reproducing the effect of microscopic near-wall region is proposed to improve computational efficiency. The surrogate model trained with Lattice Boltzmann Method(LBM) considering the rarefied effec...
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| 收稿时间： | 12 October 2020 |
A boundary surrogate model for micro/nano grooved surface structure applied in turbulence flow control over airfoil |
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| Liyue WANG,Cong WANG,Shuyue WANG,Sheng QIN,Gang SUN,Bo YOU,Yongjian ZHONG.A boundary surrogate model for micro/nano grooved surface structure applied in turbulence flow control over airfoil[J].Chinese Journal of Aeronautics,2022,35(2):62-73. |
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| Authors: | Liyue WANG Cong WANG Shuyue WANG Sheng QIN Gang SUN Bo YOU Yongjian ZHONG |
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| Institution: | 1. Department of Aeronautics & Astronautics, Fudan University, Shanghai 200433, China;2. Department of Material Science, Fudan University, Shanghai 200433, China;3. AECC Commercial Aircraft Engine Co., Ltd., Shanghai 200241, China |
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| Abstract: | The application of grooved surface structure is an emerging and effective means in tur-bulence flow control.However,for a realistic configuration,the global flow field described directly by simple application of massive grids makes it unfeasible to simulate.In this paper,a boundary surrogate model reproducing the effect of microscopic near-wall region is proposed to improve computational efficiency.The surrogate model trained with Lattice Boltzmann Method (LBM) con-sidering the rarefied effect based on real micro/nanoflow field is new among literature,which accu-rately shows flow characteristics of the micro/nano structure.With this approach,numerical simulations via Reynolds-averaged Navier Stokes equations with modified wall boundary condition are performed in subsonic and transonic flow.The results show that micro/nano grooved surface structure has the effect of delaying transition from laminar to turbulence,thus reducing the skin friction significantly.Analysis of turbulence intensity and turbulence kinetic energy shows that the near-wall flow field of grooved airfoil is more stable compared with that of the smooth airfoil.The reducing rate of maximum turbulent intensity reaches 13.39％.The paper shows a perspective for further application of micro/nano groove structure to turbulence flow control in aircraft design by providing an accurate and efficient simulation method. |
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| Keywords: | Boundary modeling CFD Drag reduction Flow control Microstructure |
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