On the Effect of Trailing-Edge Bluntness on Airfoil Noise
Keywords:airfoil noise, trailing edge bluntness.
The purpose of this study is to experimentally investigate the effect of trailing edge bluntness on the generation of airfoil tonal noise at different angles of attack and low to moderate Reynolds numbers. Detailed aeroacoustic measurements are made for an airfoil at three angles of attack: 00, 50, and 100. Airfoil chord-based Reynolds numbers analyzed are 2.8 ×105, 3.7 ×105 and 5 ×105, corresponding to free stream velocities of 14, 18 and 24 m/s, respectively. The airfoil noise with a straight trailing edge is seen to change from a broadband hump to intensive tonal noise with increasing angle of attack, while it changes from tonal noise to a broadband hump with increasing Reynolds number. Moreover, results show that for higher values of Reynolds numbers the dominant tonal peak decreases in amplitude and shifts to higher frequencies. In general, it is observed that as the trailing edge bluntness increases, the dominant tonal peaks have larger overall amplitudes.
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