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首页> 外文期刊>Journal of the American Helicopter Society >Numerical Analysis of Active Flap for Noise Reduction Using Moving Overlapped Grid Method
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Numerical Analysis of Active Flap for Noise Reduction Using Moving Overlapped Grid Method

机译：移动重叠网格法主动降噪的数值分析

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摘要

A three-dimensional unsteady Euler code for the analysis of active flap control (AFC), based upon an advanced computational fluid dynamics (CFD) code for full helicopter configurations, has been developed in this study. The effect of the AFC phase angle on blade-vortex interaction (BVI) noise is analyzed by combining the new CFD code with an acoustic code based on the Ffowcs Williams and Hawkings (FW-H) equation for the case of a one-bladed rotor with a stiff blade. As a result, the characteristic trend of noise intensity as a function of flap phase angle obtained by three-dimensional CFD calculations can be explained using a classification of two-dimensional interaction between airfoil and vortex shed from a blade with AFC. The prediction of the effect of flap phase angle by this CFD method is remarkably improved by considering the biased flow of wind tunnel. A quantitative noise reduction of 5.62 dB is obtained at the flap phase angle of 60°, where the noise signal propagates strongly almost downward for the one-bladed rotor case.
机译：在这项研究中，基于先进的计算流体动力学（CFD）代码，针对全直升机配置，开发了一种用于分析主动襟翼控制（AFC）的三维非稳态Euler代码。对于单叶片转子，通过将新的CFD代码与基于Ffowcs Williams和Hawkings（FW-H）方程的声学代码结合，分析了AFC相角对叶片-涡旋相互作用（BVI）噪声的影响用坚硬的刀片。结果，通过使用AFC对翼型和叶片涡流之间的二维相互作用进行分类，可以解释通过三维CFD计算获得的噪声强度随襟翼相位角变化的特征趋势。考虑到风洞的偏流，通过这种CFD方法对襟翼相角影响的预测得到了显着改善。襟翼相位角为60°时，可实现5.62 dB的定量降噪，其中单叶片转子壳体的噪声信号几乎向下强烈传播。

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