The effects of a morphed trailing-edge flap on the aeroacoustic and aerodynamic performance of a 30P30N Aerofoil

Watkins, Joseph; Bouferrouk, Abdessalem

Abstract

This paper presents initial results on the aeroacoustic and aerodynamic effects of morphing the trailing-edge flap of the 30P30N aerofoil, over five flap deflections (5–25◦ ), at an 8◦ angle of attack and a Reynolds number of Re = 9.2 × 105 . The Ffowcs-Williams–Hawkings acoustic analogy estimates the far-field noise, whilst the flow field is solved using URANS with the four-equation Transition SST model. Aerodynamic and aeroacoustic simulation data for the 30P30N’s full configuration compare well with experimental results. A Courant number (C) ≤ 1 should be used for resolving tonal noise, whilst a C of up to 4 is sufficient for broadband noise. Sound pressure level results show an average 11% reduction in broadband noise across all flap deflections and frequencies for the morphed configuration compared with the conventional, single-slotted flap. The morphed flap eliminates the multiple tonal peaks observed in the conventional design. Beyond 15◦ flap deflection, the morphing flap achieves higher stall angles, but with increased drag, leading to a maximum reduction of 17% in Cl /Cd ratio compared with the conventional flap. The methodology reported here for the 30P30N is a quick tool for initial estimates of the far-field noise and aerodynamic performance of a morphing flap at the design stage.

• Journal Article Type: Article
• Acceptance Date: Feb 28, 2022
• Online Publication Date: Mar 3, 2022
• Publication Date: Mar 1, 2022
• Deposit Date: Mar 4, 2022
• Publicly Available Date: Mar 8, 2022
• Journal: Acoustics
• Electronic ISSN: 2624-599X
• Publisher: MDPI
• Peer Reviewed: Peer Reviewed
• Volume: 4
• Issue: 1
• Pages: 248-267
• DOI: https://doi.org/10.3390/acoustics4010015
• Public URL: https://uwe-repository.worktribe.com/output/9099260