2023/10/16 by Mohsen Hamedi, Brian C. Vermeire, Hamedi, Mohsen +1
Engineering · #Acoustic Wave Phenomena Research #Aerodynamics and Acoustics in Jet Flows #Computational Physics (physics.comp-ph) #FOS: Physical sciences #Fluid Dynamics (physics.flu-dyn) #Fluid Dynamics and Vibration Analysis
paper · pdf · doi:10.48550/arxiv.2310.10574
openalex publication_date 2023/10/16 · openalex created_date 2025/10/10 · openalex updated_date 2026/08/02
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_∞ = 0.15, resulting in a 7.9dB noise reduction. The second case considers tandem cylinders at Re=200 and M_∞ = 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_∞ = 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.