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An aeroacoustic investigation into the effect of self-oscillating trailing edge flaplets

Talboys, E ORCID: 0000-0001-8993-0180, Geyer, T. F. & Bruecker, C. ORCID: 0000-0001-5834-3020 (2019). An aeroacoustic investigation into the effect of self-oscillating trailing edge flaplets. Journal of Fluids and Structures, 91, article number 102598. doi: 10.1016/j.jfluidstructs.2019.02.014

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The aeroacoustics of a NACA 0012 aerofoil with an array of self-oscillating flexible flaplets attached on the trailing edge has been investigated at low to moderate chord based Reynolds number (50,000 -- 350,000) and at geometric angles of attack from $\alpha_g = 0^\circ$ -- $20^\circ$. When the aerofoil is untripped, tonal peaks are observed on the baseline aerofoil. When the passive flaplets are attached to the pressure side of the aerofoil, the tonal peak is removed. If the flaplets are then placed on the suction side, the tonal peak is reduced, but not removed. It is therefore hypothesised that the flaplets on the pressure side modifies the laminar separation bubble situated on the pressure side of the aerofoil, a key mechanism for tonal noise. Throughout all cases, both tripped and untripped, a low frequency (0.1 kHz -- 0.6 kHz) noise reduction and a slight increase at higher frequencies (>2 kHz) is seen. This gives an average overall sound pressure level (OSPL) reduction of 1.5 -- 2 dB for the flaplets affixed to the pressure side. The cases where the tonal noise component is removed an OSPL reduction of up to 20 dB can be seen.

Publication Type: Article
Additional Information: © 2019 Elsevier. This manuscript version is made available under the CC-BY-NC-ND 4.0 license
Subjects: T Technology > TJ Mechanical engineering and machinery
T Technology > TL Motor vehicles. Aeronautics. Astronautics
Departments: School of Science & Technology > Engineering
SWORD Depositor:
[thumbnail of JFluidsStruc_arXiv.pdf]
Text - Accepted Version
Available under License Creative Commons Attribution Non-commercial No Derivatives.

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