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

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Abstract

Experimental results on trailing-edge (TE) noise from a NACA 633 –018 airfoil are presented for a chord-based Reynolds number Rec range between 2 × 105 and 3 × 106. Far-field TE noise from the baseline airfoil with a straight TE and TE serrations is measured with varying Rec, angle of attack, and serration shape and flap angle. Additionally, aerodynamic coefficients and boundary-layer parameters at the TE are also reported. To cover such a broad Rec range, two NACA 633 –018 airfoil models were tested in two different wind tunnels. The measurements include the emitted noise with natural and forced transition locations. For the straight TE, the forced transition location results in up to 5 dB increase of the far-field TE noise level, compared to the natural one. Scaling of the far-field noise spectra from the baseline TE shows that the Strouhal numbers St at which the peak noise level is measured reduce as Rec increases. TE noise spectra for the cases with the TE serrations are found to be dependent on the airfoil lift and Rec. The present data are to be included in the framework of the Benchmark Problems for Airframe Noise Computations category I and are publicly available in a repository with the following digital object identifier (DOI): https://doi.org/10.4121/20940646.

Original languageEnglish
Pages (from-to)329-354
Number of pages26
JournalAIAA Journal
Volume61
Issue number1
DOIs
Publication statusPublished - 2023

Bibliographical note

Green Open Access added to TU Delft Institutional Repository ‘You share, we take care!’ – Taverne project https://www.openaccess.nl/en/you-share-we-take-care
Otherwise as indicated in the copyright section: the publisher is the copyright holder of this work and the author uses the Dutch legislation to make this work public.

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