By Yu Zhou, A.D. Lucey, Yang Liu, Lixi Huang
These court cases essentially specialize in advances within the thought, experiments, and numerical simulations of turbulence within the contexts of flow-induced vibration and noise, in addition to their regulate. Fluid-related structural vibration and noise difficulties are usually encountered in lots of engineering fields, more and more making them a reason for predicament. The FSSIC convention, hung on 5-9 July 2015 in Perth, featured favourite keynote audio system akin to John Kim, Nigel Peake, track Fu and Colin Hansen, in addition to talks on a wide variety of themes: turbulence, fluid-structure interplay, fluid-related noise and the control/management points of those learn parts, a lot of that are sincerely interdisciplinary in nature. It supplied a discussion board for lecturers, scientists and engineers operating in all branches of Fluid-Structure-Sound Interactions and regulate (FSSIC) to switch and proportion the most recent advancements, principles and advances, bringing them jointly researchers from East and West to push ahead the frontiers of FSSIC, making sure that the lawsuits can be of curiosity to a wide engineering community.
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Additional info for Fluid-Structure-Sound Interactions and Control: Proceedings of the 3rd Symposium on Fluid-Structure-Sound Interactions and Control
A servo motor mounted to the rig enabled remote control of the angle-of-attack, and did not signiﬁcantly aﬀect the background noise at high ﬂow-speeds. The rig placed the airfoil several chord lengths from the exit of the nozzle (as shown in Fig. 1) in order to give a larger arc line-of-sight to the airfoil Fig. 1 Experimental setup Microphone Nozzle Motor Airfoil Rig support A Comparison of NACA 0012 and NACA 0021 Self-noise . . 5mm for future testing, and several chord lengths before the end of the plates to allow wake development.
09 m. An unequally spaced linear microphone array with 31 microphones was used to identify the sound source around airfoil and to analysis noise strength (Fig. 1). 405 m. 72 m. 015 m around 8000 Hz. A SD2030 airfoil (chord = 150 mm) with and without trailing edge serrations was used. 8). Fig. 1 Noise Source Distribution Figure 2 shows the result of noise source distributions for main ﬂow velocity of 42 m/s. Figure 2a is the background noise distribution(without airfoil). Figure 2b, c are the noise source distribution for straight/serrated trailing edge airfoil respectively.
Similar to the process of WENO reconstruction, we use nonlinear weights ωrk to replace the linear weights Ckr and obtain a nonlinear approximation. Substituting the nonlinear approximation to the linear Eq. (2), we can obtain nonlinear compact scheme. 30 S. Zhang et al. 1 Revisit the Interaction of Two Co-rotating Gaussian Vortices Gaussian vortex is a typical vortex. At some condition, two co-rotating Gaussian vortices can merge together. In the merging process, sound wave is generated. we study the merging of two co-rotating Gaussian vortices to show the superiority of our developed compact scheme.