TY - JOUR AU - Al Tlua, Basim AU - Rocha, Joana PY - 2022/07/25 Y2 - 2024/03/29 TI - On the Effect of Trailing-Edge Bluntness on Airfoil Noise JF - Canadian Acoustics JA - Canadian Acoustics VL - 50 IS - 1 SE - Article - Aeroacoustics DO - UR - https://jcaa.caa-aca.ca/index.php/jcaa/article/view/3476 SP - AB - <p><span class="Apple-converted-space"> </span>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: 0<sup>0</sup>, 5<sup>0</sup>, and 10<sup>0</sup>. Airfoil chord-based Reynolds numbers analyzed are 2.8 ×10<sup>5</sup>, 3.7 ×10<sup>5</sup> and 5 ×10<sup>5</sup>, 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.<span class="Apple-converted-space"> </span></p> ER -