Aeroacoustics investigation of a harmonically morphing trailing edge flap

Abdessemed, chawki; Yao, Yufeng; Bouferrouk, Abdessalem; Narayan, Pritesh P

Abstract

In this paper, an aeroacoustic study of a NACA 0012 airfoil fitted with a morphing Trailing Edge Flap (TEF) was performed at conditions of an Angle of Attack (AoA) = 4º, Reynolds number = 0.62×10^6 and Mach number = 0.11. A modified parametrization method was used to mathematically define the TEF deformation motion. Using the commercial software ANSYS Fluent, unsteady flow simulations were performed using a hybrid Stress Blended Eddy Simulation (SBES) RANS-LES method and the far-field noise was predicted using the Ffowcs-Williams and Hawkings (FW-H) acoustic analogy. The aerodynamic coefficients of the baseline NACA 0012 agree well with published CFD and experimental results. Furthermore, the study showed that it is possible to predict accurately the spectra of the dominant tonal frequencies. Nevertheless, the magnitude of the Sound Pressure Levels (SPL) was over-predicted by up to 22 dB. The preliminary results of an oscillating TEF at 100 Hz shows that the aerodynamic performance is practically unchanged for a 1% deflection, but for a 0.1% deflection a 2% increase in aerodynamic efficiency was achieved, despite the increase in the SPL magnitude for both cases.

• Presentation Conference Type: Conference Paper (unpublished)
• Conference Name: 53rd 3AF International Conference on Applied Aerodynamics
• Start Date: Mar 26, 2018
• End Date: Mar 28, 2018
• Acceptance Date: Mar 27, 2018
• Publication Date: Jan 1, 2018
• Peer Reviewed: Not Peer Reviewed
• Keywords: aeroacoustics, cfd, morphing, wings, airfoils, naca0012, dynamic meshing, periodic forcing, trailing edge flap
• Public URL: https://uwe-repository.worktribe.com/output/872799
• Additional Information: Title of Conference or Conference Proceedings : 53rd 3AF International Conference on Applied Aerodynamics