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| Formato: | Preprint |
| Publicado: |
2023
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| Acceso en línea: | https://arxiv.org/abs/2310.10574 |
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| _version_ | 1866912633761824768 |
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| author | Hamedi, Mohsen Vermeire, Brian |
| author_facet | Hamedi, Mohsen Vermeire, Brian |
| contents | We investigate the feasibility of gradient-free aeroacoustic shape optimization using the Flux Reconstruction (FR) approach to study two-dimensional flow at low Reynolds numbers. The Overall Sound Pressure Level (OASPL) is computed via the direct acoustic approach, and optimization is performed using the gradient-free Mesh Adaptive Direct Search (MADS) algorithm. The proposed framework is assessed across three problems. First, flow over an open cavity is investigated at a Reynolds number of $Re=1500$ and free-stream Mach number of $M_\infty = 0.15$, resulting in a $7.9dB$ noise reduction. The second case considers tandem cylinders at $Re=200$ and $M_\infty = 0.2$, achieving a $16.5 dB$ noise reduction by optimizing the distance between the cylinders and their diameter ratio. Finally, a NACA0012 airfoil is optimized at $Re=10,000$ and $M_\infty = 0.2$ to reduce trailing edge noise. The airfoil's shape is optimized to generate a new 4-digit NACA airfoil at an appropriate angle of attack to reduce OASPL while maintaining the baseline time-averaged lift coefficient and preventing an increase in the baseline time-averaged drag coefficient. The optimized airfoil is silent at $0dB$ and the drag coefficient is decreased by $24.95\%$. These results demonstrate the feasibility of shape optimization using MADS and FR for aeroacoustic design. |
| format | Preprint |
| id |
arxiv_https___arxiv_org_abs_2310_10574 |
| institution | arXiv |
| publishDate | 2023 |
| record_format | arxiv |
| spellingShingle | Near-Field Aeroacoustic Shape Optimization at Low Reynolds Numbers Hamedi, Mohsen Vermeire, Brian Fluid Dynamics Computational Physics We investigate the feasibility of gradient-free aeroacoustic shape optimization using the Flux Reconstruction (FR) approach to study two-dimensional flow at low Reynolds numbers. The Overall Sound Pressure Level (OASPL) is computed via the direct acoustic approach, and optimization is performed using the gradient-free Mesh Adaptive Direct Search (MADS) algorithm. The proposed framework is assessed across three problems. First, flow over an open cavity is investigated at a Reynolds number of $Re=1500$ and free-stream Mach number of $M_\infty = 0.15$, resulting in a $7.9dB$ noise reduction. The second case considers tandem cylinders at $Re=200$ and $M_\infty = 0.2$, achieving a $16.5 dB$ noise reduction by optimizing the distance between the cylinders and their diameter ratio. Finally, a NACA0012 airfoil is optimized at $Re=10,000$ and $M_\infty = 0.2$ to reduce trailing edge noise. The airfoil's shape is optimized to generate a new 4-digit NACA airfoil at an appropriate angle of attack to reduce OASPL while maintaining the baseline time-averaged lift coefficient and preventing an increase in the baseline time-averaged drag coefficient. The optimized airfoil is silent at $0dB$ and the drag coefficient is decreased by $24.95\%$. These results demonstrate the feasibility of shape optimization using MADS and FR for aeroacoustic design. |
| title | Near-Field Aeroacoustic Shape Optimization at Low Reynolds Numbers |
| topic | Fluid Dynamics Computational Physics |
| url | https://arxiv.org/abs/2310.10574 |