孔腔流动中含有复杂的流体振荡,不但能够引起明显的噪声,而且会造成物体脉动压力和阻力的急剧增加,因而孔腔流动与流激噪声已经成为流声耦合研究领域的重要内容。文章首先对于Powell涡声理论进行了介绍,给出了涡声方程及其求解的详细推...孔腔流动中含有复杂的流体振荡,不但能够引起明显的噪声,而且会造成物体脉动压力和阻力的急剧增加,因而孔腔流动与流激噪声已经成为流声耦合研究领域的重要内容。文章首先对于Powell涡声理论进行了介绍,给出了涡声方程及其求解的详细推导过程,随后利用圆柱/机翼组合体与方腔流激噪声测试结果验证了计算方法的可靠性,最后采用大涡模拟方法结合Powell涡声方程数值计算了两型孔腔在不同水速下的流激噪声,并与中国船舶科学研究中心循环水槽试验结果进行了对比分析,结果表明数值计算方法能够较准确地预报孔腔流激噪声,并能展示孔腔内外涡旋结构。计算结果表明:在500 Hz以下的低频段,格栅1型孔腔的流激噪声显著高于格栅2型孔腔;在500 Hz-10 k Hz高频段,格栅2型孔腔流激噪声比格栅1型孔腔高,但随着流速的增高,两种孔腔流激噪声在高频段的幅值基本一致。这些现象与孔腔内的涡旋结构密切相关。文中对孔腔流激噪声的数值预报方法进行了验证,有益于理解孔腔非定常流动的物理机理,且为抑制孔腔流激噪声奠定了基础。展开更多
The sound generated by a NACA0012 airfoil in the wake of a rod is numerically simulated by two approaches, one is the large eddy simulation （LES） with the FW-H acoustic analogy and the other is the LES with the Powe...The sound generated by a NACA0012 airfoil in the wake of a rod is numerically simulated by two approaches, one is the large eddy simulation （LES） with the FW-H acoustic analogy and the other is the LES with the Powell vortex sound theory, in order to compare the accuracies of their predictions. The vortical structures around the rod-airfoil are computed by the LES and captured by the vortex identification （Q）. The acoustic predictions are verified by the measurements. It is shown that the computed results by the two hybrid approa- ches （LES and FW-H, LES and Powell） are very similar. Both are shown to be satisfactory in the prediction of the noise generated by an unsteady flow. Subsequently, the numerical simulations of the wall pressure fluctuations and the flow-induced noise of a NACA0015 airfoil are made by the two hybrid approaches. At two angles of attack （ 0~ and 8~ ）, the wall pressure fluctuations of the NACA0015 airfoil are computed. The obtained power spectra of the wall pressure fluctuations are analyzed and compared with the measured data. And the vortical structures around the airfoil at two angles of attack are simulated and analyzed. After that, the flow induced noises of the NACA0015 airfoil at two angles of attack are predicted by the two hybrid approaches （LES and FW-H, LES and Powell）. The radiated sound spectra are analyzed and compared with the experimental data. Comparisons show that both are robust, credible and satisfactory in the numerical prediction of the flow induced noise. All numerical simulations are carried out by parallel processing in the Wuxi supercomputing center.展开更多
In this paper, the measurement of an aerodynamic sound source for a semi-circular cylinder in a uniform flow is described using Particle Image Velocimetry (PIV). This experimental technique is based on vortex sound th...In this paper, the measurement of an aerodynamic sound source for a semi-circular cylinder in a uniform flow is described using Particle Image Velocimetry (PIV). This experimental technique is based on vortex sound theory, where the time derivative of vorticity is evaluated with the aid of two sets of standard PIV systems. The experimental results indicate that the sound source for the semi-circular cylinder is located around the shear layer near the edge of the semi-circular cylinder. The sound source intensity and the area are reduced in the semi-circular cylinder compared with those of a circular cylinder. This result indicates that the aerodynamic sound of the semi- circular cylinder is smaller than that of the circular cylinder, which supports the microphone measurement result.展开更多
文摘孔腔流动中含有复杂的流体振荡,不但能够引起明显的噪声,而且会造成物体脉动压力和阻力的急剧增加,因而孔腔流动与流激噪声已经成为流声耦合研究领域的重要内容。文章首先对于Powell涡声理论进行了介绍,给出了涡声方程及其求解的详细推导过程,随后利用圆柱/机翼组合体与方腔流激噪声测试结果验证了计算方法的可靠性,最后采用大涡模拟方法结合Powell涡声方程数值计算了两型孔腔在不同水速下的流激噪声,并与中国船舶科学研究中心循环水槽试验结果进行了对比分析,结果表明数值计算方法能够较准确地预报孔腔流激噪声,并能展示孔腔内外涡旋结构。计算结果表明:在500 Hz以下的低频段,格栅1型孔腔的流激噪声显著高于格栅2型孔腔;在500 Hz-10 k Hz高频段,格栅2型孔腔流激噪声比格栅1型孔腔高,但随着流速的增高,两种孔腔流激噪声在高频段的幅值基本一致。这些现象与孔腔内的涡旋结构密切相关。文中对孔腔流激噪声的数值预报方法进行了验证,有益于理解孔腔非定常流动的物理机理,且为抑制孔腔流激噪声奠定了基础。
文摘The sound generated by a NACA0012 airfoil in the wake of a rod is numerically simulated by two approaches, one is the large eddy simulation （LES） with the FW-H acoustic analogy and the other is the LES with the Powell vortex sound theory, in order to compare the accuracies of their predictions. The vortical structures around the rod-airfoil are computed by the LES and captured by the vortex identification （Q）. The acoustic predictions are verified by the measurements. It is shown that the computed results by the two hybrid approa- ches （LES and FW-H, LES and Powell） are very similar. Both are shown to be satisfactory in the prediction of the noise generated by an unsteady flow. Subsequently, the numerical simulations of the wall pressure fluctuations and the flow-induced noise of a NACA0015 airfoil are made by the two hybrid approaches. At two angles of attack （ 0~ and 8~ ）, the wall pressure fluctuations of the NACA0015 airfoil are computed. The obtained power spectra of the wall pressure fluctuations are analyzed and compared with the measured data. And the vortical structures around the airfoil at two angles of attack are simulated and analyzed. After that, the flow induced noises of the NACA0015 airfoil at two angles of attack are predicted by the two hybrid approaches （LES and FW-H, LES and Powell）. The radiated sound spectra are analyzed and compared with the experimental data. Comparisons show that both are robust, credible and satisfactory in the numerical prediction of the flow induced noise. All numerical simulations are carried out by parallel processing in the Wuxi supercomputing center.
文摘In this paper, the measurement of an aerodynamic sound source for a semi-circular cylinder in a uniform flow is described using Particle Image Velocimetry (PIV). This experimental technique is based on vortex sound theory, where the time derivative of vorticity is evaluated with the aid of two sets of standard PIV systems. The experimental results indicate that the sound source for the semi-circular cylinder is located around the shear layer near the edge of the semi-circular cylinder. The sound source intensity and the area are reduced in the semi-circular cylinder compared with those of a circular cylinder. This result indicates that the aerodynamic sound of the semi- circular cylinder is smaller than that of the circular cylinder, which supports the microphone measurement result.
