Aeroacoustic Benchmarking of Trailing-Edge Noise from NACA 633–018 Airfoil with Trailing-Edge Serrations

Experimental results on trailing-edge (TE) noise from a NACA [Formula: see text] airfoil are presented for chord-based Reynolds number range between and text]. Far-field TE the baseline with straight serrations is measured varying text], angle of attack, serration shape flap angle. Additionally, aerodynamic coefficients boundary-layer parameters at also reported. To cover such broad range, two models were tested in different wind tunnels. The measurements include emitted natural forced transition locations. For TE, location up to 5 dB increase far-field level, compared one. Scaling spectra shows that Strouhal numbers which peak level reduce as increases. cases found be dependent lift present data included framework Benchmark Problems Airframe Noise Computations category I publicly available repository following digital object identifier (DOI): https://doi.org/10.4121/20940646 .