Effect of Angle of Attack and Excitation Frequency on Pressure, Velocity, Sound Pressure Level, and Transmission Loss Around a NACA 0012 Airfoil: A Numerical Study
Document Type : Original Research
Authors
1
University of Bonab
2
School of Mechanical Engineering, University of Tabriz, Tabriz, Iran
10.48311/jaert.2026.120185.82808
Abstract
The current numerical study analyzes the aero-acoustic behavior of a NACA 0012 airfoil using the finite element method with the SST k−ω turbulence model. The influence of various parameters such as angle of attack (from 0∘ to 14∘), excitation frequency (from 10100 Hz to 59600 Hz), and Reynolds number (from 2×106 to 10×106) on pressure, velocity, SPL, and TL is considered. The numerical simulation is verified by comparing with available experimental results, and there is a reasonable agreement between both datasets. It is revealed that the increase of the angle of attack raises lift but induces flow separation at an angle of attack of 14∘. The acoustic performance increases by increasing the angle of attack and excitation frequency. The maximum TL reaches 19.4 dB at an angle of attack of 14∘ and 21.3 dB at the excitation frequency of 59600 Hz. On the other hand, the rise of Reynolds number reduces TL; for example, TL equals 18.6 dB at Re=2×106 and 13.2 dB at Re=10×106.
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