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粗糙带圆柱尾迹流场中翼型噪声的数值研究
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Abstract:
通过数值模拟方法研究了不同高度粗糙带圆柱下尾迹变化，以及粗糙带对圆柱和翼型的气动性能和噪声的影响。高粗糙带下的圆柱升阻力系数更大，低粗糙带则影响较小，粗糙带对翼型的升阻力系数影响较小，高粗糙带在一定区域会提高翼型的表面时间平均压力系数。并且高粗糙带会改变圆柱表面的边界层分离后的流动和低速回流区的范围，增强扰动影响后方翼型流场。FW-H方程积分不同表面得到远场位置声压级，在90？位置高粗糙带会增加圆柱和翼型噪声，在60？位置积分面只有翼型时，高粗糙带圆柱后方翼型的噪声反而更小。还比较了局部流场和全局流场的压力脉动均方根值，表明高粗糙带圆柱后方流场有更强的声源强度，最后分析了瞬时涡结构和湍流强度的变化，表明高粗糙带对后方尾迹具体扰动。
The change of wake under the cylinder with different height rough band and the influence of rough band on the aerodynamic performance and noise of the cylinder and airfoil are studied by numeri-cal simulation. The cylindrical drag coefficient under the high rough zone is greater, while the low rough zone has little influence on the drag coefficient of the airfoil. The high rough zone will increase the surface time average pressure coefficient of the airfoil in a certain area. In addition, the high roughness zone will change the flow range after boundary layer separation on the cylindrical sur-face and the low velocity reflux zone, and enhance the disturbance influence on the rear airfoil flow field. FW-H equation is integrated with different surfaces to obtain sound pressure levels at far-field positions. The noise of cylinder and airfoil is increased at 90？ with high roughness band, but the noise of airfoil behind the cylinder with high roughness band is smaller at 60？ with only airfoil as integral surface. The root mean square value of pressure pulsation of local and global flow fields is also compared, indicating that the flow field behind the cylinder with high rough zone has stronger sound source intensity. Finally, the changes of instantaneous vortex structure and turbulence in-tensity are analyzed, indicating that the high rough zone has specific disturbance to the rear wake.
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