Experimental Investigation of the Flow Characteristics and Noise Generation at the Wing–Wall Junction

Ding, Yuchen; Zhang, T; Geyer, Thomas; Silva, C M de; Doolan, Con J.; Moreau, Danielle

doi:10.1061/(asce)as.1943-5525.0001303

Cited by 1 publication

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“…The relatively high noise levels at the wing-wall junction region above 10 kHz (𝑆𝑡 𝑐 ≥ 22.5) shown in Figs. 10(h-i) are likely caused by the interaction between the horseshoe vortex generated at the LE-wall junction and the thin LE, which has been reported by Ding et al [28]. Figure 11 presents the one-twelfth octave band noise spectra showing the contribution of the tip noise to the noise produced by the entire wing, compared with other wing regions defined previously in Fig.…”

Section: Resultsmentioning

confidence: 64%

Wing Tip Vortex Formation Noise

Zhang

Moreau

Doolan

et al. 2022

28th AIAA/CEAS Aeroacoustics 2022 Conference

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In this study, the far-field acoustics and near-field flow characterizing vortex formation at a wing tip has been investigated experimentally. Measurements have been taken on a rectangular planform NACA 0012 wing with a flat tip and an aspect ratio (span-to-chord ratio) of 𝐴𝑅 = 𝑠/𝑐 = 2 at a Reynolds number of 𝑅𝑒 = 1.5 × 10 4 , and a geometric angle of attack of 𝛼 = 5 • in the UNSW anechoic wind tunnel. Acoustic beamforming results obtained with a planar 64-microphone array show that tip noise is a prominent airfoil noise source at mid to high frequencies (3.7 to 11.5 kHz), corresponding to chord-based Strouhal numbers of 𝑆𝑡 𝑐 = 𝑓 𝑐/𝑈 ∞ = 8 − 25. Stereoscopic Particle Image Velocimetry measurements reveal information about the size and location of the tip vortex in the near wake. In the vortex core, the axial velocity has a wake-like profile with a velocity deficit of 24%. Snapshot Proper Orthogonal Decomposition is used to extract the dominant coherent structures, which reveals that the two most energetic modes are found to consist of a coherent structure pair within the vortex core region. The unsteady surface pressure field over the wing tip is measured using the remote microphone technique. High magnitude pressure fluctuations are observed near the trailing edge on the tip surface and on the airfoil suction side that may be associated with the tip noise source.

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Section: Resultsmentioning

confidence: 64%