Tonal noise production from a wall-mounted finite airfoil

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• 作者：Danielle J. Moreau ; ^{d.moreau@unsw.edu.au" class="auth_mail" title="E-mail the corresponding author} ; Con J. Doolan ^{c.doolan@unsw.edu.au" class="auth_mail" title="E-mail the corresponding author}
• 刊名：Journal of Sound and Vibration
• 出版年：2016
• 出版时间：17 February 2016
• 年：2016
• 卷：363
• 期：Complete
• 页码：199-224
• 全文大小：9011 K

文摘

This study is concerned with the flow-induced noise of a smooth wall-mounted finite airfoil with flat ended tip and natural boundary layer transition. Far-field noise measurements have been taken at a single observer location and with a microphone array in the Virginia Tech Stability Wind Tunnel for a wall-mounted finite airfoil with aspect ratios of L/C=1–3$L/C=1–3$, at a range of Reynolds numbers (Re_C=7.9×10⁵–1.6×10⁶${\mathit{Re}}_C=7.9\times {10}^5–1.6\times {10}^6$, based on chord) and geometric angles of attack (α=0–6°)$(\alpha =0–6°)$. At these Reynolds numbers, the wall-mounted finite airfoil produces a broadband noise contribution with a number of discrete equispaced tones at non-zero angles of attack. Spectral data are also presented for the noise produced due to three-dimensional vortex flow near the airfoil tip and wall junction to show the contributions of these flow features to airfoil noise generation. Tonal noise production is linked to the presence of a transitional flow state to the trailing edge and an accompanying region of mildly separated flow on the pressure surface. The separated flow region and tonal noise source location shift along the airfoil trailing edge towards the free-end region with increasing geometric angle of attack due to the influence of the tip flow field over the airfoil span. Tonal envelopes defining the operating conditions for tonal noise production from a wall-mounted finite airfoil are derived and show that the domain of tonal noise production differs significantly from that of a two-dimensional airfoil. Tonal noise production shifts to lower Reynolds numbers and higher geometric angles of attack as airfoil aspect ratio is reduced.